# Patent

## Title
Fe-based metal plate and method of manufacturing the same

## Abstract

On at least one surface of a base metal plate (1) of an α-γ transforming Fe or Fe alloy, a metal layer (2) containing ferrite former is formed. Next, the base metal plate (1) and the metal layer (2) are heated to an A3 point of the Fe or the Fe alloy, whereby the ferrite former are diffused into the base metal plate (1) to form an alloy region (1b) in a ferrite phase in which an accumulation degree of {200} planes is 25% or more and an accumulation degree of {222} planes is 40% or less. Next, the base metal plate (1) is heated to a temperature higher than the A3 point of the Fe or the Fe alloy, whereby the accumulation degree of the {200} planes is increased and the accumulation degree of the {222} planes is decreased while the alloy region (11b) is maintained in the ferrite phase.

## Background
This application is a national stage application of International Application No. PCT/JP2010/069102, filed Oct. 27, 2010, which claims priority to Japanese Application No. 2009-248057, filed Oct. 28, 2009, the content of which is incorporated by reference in its entirety.
TECHNICAL FIELD
The present invention relates to a Fe-based metal plate used for a magnetic core or the like and a method of manufacturing the same.
BACKGROUND ART
Silicon steel plates have been conventionally used for magnetic cores of electric motors, power generators, transformers, and the like. A silicon steel plate used for a magnetic core is required to be small in magnetic energy loss (core loss) in an alternating magnetic field and to be high in magnetic flux density in practical magnetic fields. To realize these, it is effective to increase electric resistance and to accumulate <100> axes being a direction of easy magnetization of αFe, in a direction of a used magnetic field. Especially when {100} planes of αFe are highly accumulated in a surface (rolled surface) of a silicon steel plate, <100> axes are highly accumulated in the rolled surface, so that higher magnetic flux density can be obtained. Therefore, there have been proposed various techniques aiming at the higher accumulation of {100} planes in a surface of a silicon steel plate.
However, the conventional techniques have difficulty in realizing the stable high accumulation of [100] planes in a surface of a Fe-based metal plate such as a silicon steel plate.
CITATION LIST
Patent Literature
Patent Literature 1: Japanese Laid-open Patent Publication No. 01-252727
Patent Literature 2: Japanese Laid-open Patent Publication No. 05-279740
Patent Literature 3: Japanese Laid-open Patent Publication No. 2007-51338
Patent Literature 4: Japanese Laid-open Patent Publication No. 2006-144116
Patent Literature 5: Japanese National Publication of International Patent Application No. 2010-513716
SUMMARY OF INVENTION
Technical Problem
It is an object of the present invention to provide a Fe-based metal plate capable of having higher magnetic flux density and a method of manufacturing the same.
Solution to Problem
(1) A method of manufacturing an Fe-based metal plate including:

    
    
        forming a metal layer containing ferrite former on at least one surface of a base metal plate of an α-γ transforming Fe or Fe alloy;
        next heating the base metal plate and the metal layer to an A3 point of the Fe or the Fe alloy so as to diffuse the ferrite former into the base metal plate and form an alloy region of a ferrite phase in which an accumulation degree of {200} planes is 25% or more and an accumulation degree of {222} planes is 40% or less; and
        next heating the base metal plate to a temperature equal to or higher than the A3 point of the Fe or the Fe alloy so as to increase the accumulation degree of the {200} planes and decrease the accumulation degree of the {222} planes while maintaining the alloy region of the ferrite phase.
    
    


(2) The method of manufacturing an Fe-based metal plate according to (1), including, after the increasing the accumulation degree of the {200}planes and the decreasing the accumulation degree of the {222} planes, cooling the base metal plate to a temperature lower than the A3 point of the Fe or the Fe alloy so as to transform an unalloyed region in the base metal plate from an austenitic phase to a ferrite phase, further increase the accumulation degree of the {200} planes and further decrease the accumulation degree of the {222} planes.
(3) The method of manufacturing an Fe-based metal plate according to (1) or (2), wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the accumulation degree of the {200} planes is increased to 30% or more and the accumulation degree of the {222} planes is decreased to 30% or less.
(4) The method of manufacturing an Fe-based metal plate according to (1) or (2), wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the accumulation degree of the {200} planes is increased to 50% or more and the accumulation degree of the {222} planes is decreased to 15% or less.
(5) The method of manufacturing an Fe-based metal plate according to any one of (1) to (4), wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the ferrite former contained in the metal layer are all diffused into the base metal plate.
(6) The method of manufacturing an Fe-based metal plate according to any one of (1) to (5), wherein the ferrite former are at least one kind selected from a group consisting of Al, Cr, Ga, Ge, Mo, Sb, Si, Sn, Ti, V, W, and Zn.
(7) The method of manufacturing an Fe-based metal plate according to any one of (1) to (6), wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, an area ratio of a ferrite single phase region to the metal plate in a cross section in a thickness direction is made to 1% or more.
(8) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a working strain is brought about and in which dislocation density is not less than 1×1015 m/m3 nor more than 1×1017 m/m3.
(9) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a working strain is brought about by cold rolling in which rolling reduction ratio is not less than 97% nor more than 99.99%.
(10) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a working strain is brought about by shot blasting.
(11) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a working strain is brought about by cold rolling in which rolling reduction ratio is not less than 50% nor more than 99.99% and shot blasting.
(12) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a shear strain of 0.2 or more is brought about by cold rolling.
(13) The method of manufacturing an Fe-based metal plate according to any one of (1) to (7), wherein as the base metal plate, used is one in which a shear strain of 0.1 or more is brought about by cold rolling and a working strain is brought about by shot blasting.
(14) The method of manufacturing an Fe-based metal plate according to any one of (1) to (13), wherein a thickness of the base metal plate is not less than 10 μm nor more than 5 mm.
(15) A Fe-based metal plate, containing ferrite former, wherein, in a surface, an accumulation degree of {200} planes in a ferrite phase is 30% or more and an accumulation degree of {222} planes in the ferrite phase is 30% or less.
(16) The Fe-based metal plate according to (15), being formed by diffusion of the ferrite former from a surface to an inner part of an α-γ transforming Fe or Fe alloy plate.
(17) The Fe-based metal plate according to (15) or (16), including, on the surface, a metal layer containing the ferrite former.
(18) The Fe-based metal plate according to any one of (15) to (17), wherein the accumulation degree of the {200} planes is 50% or more and the accumulation degree of the {222} planes is 15% or less.
(19) The Fe-based metal plate according to any one of (15) to (18), wherein the ferrite former are at least one kind selected from a group consisting of Al, Cr, Ga, Ge, Mo, Sb, Si, Sn, Ti, V, W, and Zn.
(20) The Fe-based metal plate according to any one of (15) to (19), including a 1% ferrite single phase region or more in terms of an area ratio in a thicknesswise cross section of the metal plate.
The accumulation degree of the {200} planes in the ferrite phase is expressed by an expression (1) and the accumulation degree of the {222} planes in the ferrite phase is expressed by an expression (2).

accumulation degree of {200}planes=[{i(200)/I(200)}/Σ{i(hkl)/I(hkl)}]×100  (1)

accumulation degree of {222}planes=[{i(222)/I(222)}/Σ{i(hkl)/I(hkl)}]×100  (2)

Here, i(hkl) is actually measured integrated intensity of {hkl} planes in the surface of the Fe-based metal plate or the base metal plate, and I(hkl) is theoretical integrated intensity of {hkl} planes in a sample having random orientation. As the (hkl) planes, used are, for examples, 11 kinds of {110}, {200}, {211}, {310}, {222}, {321}, {411}, {420}, {332}, {521}, and {442} planes.
Advantageous Effects of Invention
According to the present invention, it is possible to obtain a Fe-based metal plate in which an accumulation degree of {200} planes in a ferrite phase is high and an accumulation degree of {222} planes in the ferrite phase is low, and to improve magnetic flux density.



BRIEF DESCRIPTION OF DRAWINGS
FIG. 1A is a cross-sectional view showing a basic principle of the present invention.
FIG. 1B which continues from FIG. 1A, is a cross-sectional view showing the basic principle of the present invention.
FIG. 1C, which continues from FIG. 1B, is a cross-sectional view showing the basic principle of the present invention.
FIG. 1D, which continues from FIG. 1C, is a cross-sectional view showing the basic principle of the present invention.
FIG. 1E, which continues from FIG. 1D, is a cross-sectional view showing the basic principle of the present invention.
FIG. 2A is a cross-sectional view showing a method of manufacturing a Fe-based metal plate according to a first embodiment.
FIG. 2B, which continues from FIG. 2A, is a cross-sectional view showing the method of manufacturing the Fe-based metal plate.
FIG. 2C, which continues from FIG. 2B, is a cross-sectional view showing the method of manufacturing the Fe-based metal plate.
FIG. 2D, which continues from FIG. 2C, is a cross-sectional view showing the method of manufacturing the Fe-based metal plate.
FIG. 3 is a cross-sectional view showing a method of manufacturing a Fe-based metal plate according to a second embodiment.
FIG. 4 is a cross-sectional view showing a method of manufacturing a Fe-based metal plate according to a third embodiment.



DESCRIPTION OF EMBODIMENTS
(Basic Principle of Present Invention)
First, a basic principle of the present invention will be described. FIG. 1A to FIG. 1E are cross-sectional views showing the basic principle of the present invention.
In the present invention, for example, as illustrated in FIG. 1A, a metal layer 2 containing ferrite former is formed on at least one surface of a base metal plate 1 composed of an α-γ transforming Fe-based metal (Fe or Fe alloy). As the base metal plate 1, for example, pure iron plate cold-rolled with a very high rolling reduction ratio of about 99.8% is used. Further, as the metal layer 2, an Al layer is formed, for example.
Next, the base metal plate 1 and the metal layer 2 are heated to the A3 point of the material (pure iron) of the base metal plate 1. During the heating, as illustrated in FIG. 1B, Al being the ferrite former in the metal layer 2 is diffused into the base metal plate 1, so that an alloy region 1b in a ferrite phase (α phase) is formed. The remainder of the base metal plate 1 is an unalloyed region 1a in the α phase until an instant immediately before the A3 point is reached. In accordance with the heating, recrystallization occurs in the alloy region 1b and the unalloyed region 1a. Further, since a large strain has been generated due to the cold rolling, planes parallel to a surface of the base metal plate 1 (rolled surface), of grains generated by the recrystallization are likely to be oriented in {100}. Therefore, many grains whose planes parallel to the rolled surface are oriented in {100} are generated both in the alloy region 1b and the unalloyed region 1a. Here, important points of the present invention are that, by the instant before the temperature reaches the A3 point, α-phase grains oriented in {100} are contained in the alloy region 1b due to the diffusion of Al being the ferrite former, and that the alloy region 1b has the α single phase alloy composition.
Thereafter, the base metal plate 1 and the metal layer 2 are further heated to a temperature equal to or higher than the A3 point of the pure iron. As a result, as illustrated in FIG. 1C, the unalloyed region 1a composed of the pure iron is γ-transformed to become an austenitic phase (γ phase), while the alloy region 1b containing Al being the ferrite former is maintained in the α phase. Even at the temperature equal to or higher than the A3 point, the α-phase grains oriented in {100}, which are formed at lower than the A3 point, do not undergo the γ-transformation and their crystal orientation is maintained. Further, in the alloy region 1b, grains 3 whose planes parallel to the rolled surface are oriented in {100} predominantly grow. Along with the growth of the {100} grains, grains oriented in other directions vanish. For example, grains whose planes parallel to the rolled surface are oriented in {111} decrease. Therefore, in the alloy region 1b, the accumulation degree of {200} planes in the α phase increases and the accumulation degree of {222} planes in the α phase decreases.
Then, when the base metal plate 1 and the metal layer 2 are kept at the temperature equal to or higher than the A3 point of the pure iron, Al in the metal layer 2 further diffuses into the base metal plate 1, and as illustrated in FIG. 1D, the alloy region 1b in the α phase expands. That is, in accordance with the diffusion of Al being the ferrite former, part of the unalloyed region 1a in the γ phase changes to the alloy region 1b in the α phase. At the time of this change, since the alloy region 1b being a region adjacent to a metal layer 2 side of the region where the change occurs has already been oriented in {100}, the region where the change occurs takes over the crystal orientation of the alloy region 1b to be oriented in {100}. As a result, the grains 3 whose planes parallel to the rolled surface are oriented in {100} further grow. Then, along with the growth of the grains 3, the accumulation degree of the {200} planes in the α phase further increases and the accumulation degree of the {222} planes in the α phase further decreases.
Subsequently, the base metal plate 1 is cooled to a temperature lower than the A3 point of the pure iron. As a result, as illustrated in FIG. 1E, the unalloyed region 1a composed of the pure iron is α-transformed to the α phase. At the time of the phase transformation as well, since the alloy region 1b being the region adjacent to the metal layer 2 side of the region where the phase transformation occurs has already been oriented in {100}, the region where the phase transformation occurs takes over the crystal orientation of the alloy region 1b to be oriented in {100}. As a result, the grains 3 whose planes parallel to the rolled surface are oriented in {100} further grow. Then, along with the growth of the grains 3, the accumulation degree of the {200} planes in the α phase further increases and the accumulation degree of the {222} planes in the α phase further decreases. That is, a high accumulation degree of the {200} planes in the α phase is obtained also in the unalloyed region 1a. 
Incidentally, when the metal layer 2 is thick and the keeping time of the temperature equal to or higher than the A3 point is long, Al sufficiently diffuses and the unalloyed region 1a sometimes disappears before the temperature of the base metal plate 1 reaches lower than the A3 point at the time of the cooling. In this case, the phase transformation of the unalloyed region 1a does not occur, and since the whole region has become the alloy region 1b, the state at the start of the cooling is maintained.
Therefore, in the Fe-based metal plate (Fe or Fe alloy plate) manufactured through these processes, the accumulation degree of the {200} planes in the α phase is extremely high and the accumulation degree of the {222} planes in the α phase is extremely low. Therefore, high magnetic flux density is obtained.
Here, conditions in the present invention will be described.
“Base Metal Plate”
As a material of the base metal plate, an α-γ transforming Fe-based metal (Fe or Fe alloy) is used. The Fe-based metal contains, for example, 70 mass % Fe or more. Further, the α-γ transformation series is, for example, a component series which has the A3 point within a range of about 600° C. to 1000° C., and which has an α phase as its main phase at lower than the A3 point and has a γ phase as its main phase at the A3 point or higher. Here, the main phase refers to a phase whose volume ratio is over 50%. The use of the α-γ transforming Fe-based metal makes it possible to form a region having an α single phase composition in accordance with the diffusion and alloying of a ferrite former. Examples of the α-γ transforming Fe-based metal may be pure iron, low-carbon steel, and the like. For example, usable is pure iron whose C content is 1 mass ppm to 0.2 mass %, with the balance being Fe and inevitable impurities. Also usable is silicon steel composed of an α-γ transforming component whose basic components are C with a 0.1 mass % content or less and Si with a 0.1 mass % to 2.5 mass % content. Further, any of these to which various kinds of elements are added may also be used. Examples of the various elements are Mn, Ni, Cr, Al, Mo, W, V, Ti, Nb, B, Cu, Co, Zr, Y, Hf, La, Ce, N, O, P, S, and so on. However, it is preferable that Mn and Ni are not contained because they may involve a risk of lowering magnetic flux density.
As the base metal plate, one in which a strain is brought about is used, for example. This is intended to generate many grains whose planes parallel to the rolled surface are oriented in {100}, at the time of the recrystallization of the base metal plate, thereby improving the accumulation degree of the {200} planes in the α phase. For example, it is preferable to bring about a working strain with which dislocation density becomes not less than 1×1015 m/m3 nor more than 1×1017 m/m3. A method for generating such a strain is not particularly limited, but, for example, it is preferable to apply cold rolling with a high rolling reduction ratio, especially with a rolling reduction ratio of not less than 97% nor more than 99.99%. Alternatively, a shear strain of 0.2 or more may be generated by cold rolling. It is possible to generate the shear strain by, for example, rotating upper and lower reduction rolls at different speeds at the time of the cold rolling. In this case, the larger a difference in the rotation speed between the upper and lower reduction rolls, the larger the shear strain. The shear strain may be calculated from diameters of the reduction rolls and a difference in rotation speed therebetween.
The strain need not exist all along the thickness direction of the base metal plate, and the strain only needs to exist in a portion where the formation of the alloyed region starts, that is, in a surface layer portion of the base metal plate. Therefore, the working strain may be brought about by shot blasting, or the generation of the working strain or the generation of the shear strain by the cold rolling may be combined with the generation of the working strain by the shot blasting. When the cold rolling and the shot blasting are combined, a rolling reduction ratio of the cold rolling may be not less than 50% nor more than 99.99%. When the generation of the shear strain and the shot blasting are combined, the shear strain may be 0.1 or more. When the working strain is brought about by the shot blasting, it is possible to make the orientation of the {100} planes of the grains uniform in planes parallel to the surface of the Fe-based metal plate.
As the base metal plate, one in which a texture oriented in {100} is formed in the surface layer portion in advance may be used, for example. In this case as well, in the alloy region, it is possible to increase the accumulation degree of the {200} planes in the α phase and decrease the accumulation degree of the {222} planes in the α phase. It is possible to obtain such a base metal plate by, for example, subjecting a metal plate including a large strain to recrystallization annealing.
Though details will be described later, a base metal plate may be used in which an α-phase alloy region where the accumulation degree of the {200} planes in the α phase is 25% or more and the accumulation degree of the {222} planes in the α phase is 40% or less is formed at the time of the heating to the A3 point.
A thickness of the base metal plate is preferably not less than 10 μm nor more than 5 mm, for example. As will be described later, a thickness of the Fe-based metal plate is preferably more than 10 μm and 6 mm or less. Considering that the metal layer is formed, when the thickness of the base metal plate is not less than 10 μm nor more than 5 mm, the thickness of the Fe-based metal plate may be easily more than 10 μm and 6 mm or less.
“Ferrite former and Metal Layer”
As the ferrite former, Al, Cr, Ga, Ge, Mo, Sb, Si, Sn, Ta, Ti, V, W, Zn, or the like is preferably used. The use of any of these elements facilitates forming the region having the α single phase composition and makes it possible to efficiently enhance the accumulation degree of the {200} planes in the α phase.
A method of forming the metal layer containing the ferrite former is not particularly limited, and examples thereof may be plating methods such as a hot dipping method and an electrolytic plating method, dry process methods such as a PVD (physical vapor deposition) method and a CVD (chemical vapor deposition) method, a rolling clad method, powder coating, and so on. Among them, the plating method and the rolling clad method are preferable especially when the method is industrially implemented. This is because they may easily and efficiently form the metal layer.
A thickness of the metal layer is preferably not less than 0.05 μm nor more than 1000 μm. When the thickness of the metal layer is less than 0.05 μm, it may be difficult to sufficiently form the alloy region and it is not sometimes possible to obtain the sufficient accumulation degree of the {200} planes in the α phase. Further, when the thickness of the metal layer is over 1000 μm, the metal layer sometimes remains thickly after the cooling to lower than the A3 point and a high magnetic property cannot be sometimes obtained.
“Ratio of Alloying of Metal Layer”
In the metal layer, a ratio of its portion alloyed with the base metal plate is preferably 10% or more in the thickness direction. When the ratio is less than 10%, it may be difficult to sufficiently form the alloy region and it is not sometimes possible to obtain the sufficient accumulation degree of the {200} planes in the α phase. Incidentally, the ratio (alloying ratio) may be expressed by an expression (3), where S0 is an area of the metal layer before the heating in a cross section perpendicular to the surface of the base metal plate and S is an area of the metal layer after the heating and the cooling.

alloying ratio=((S0−S)/S0)×100  (3)

“Ratio of α Single Phase Region”
The region having the α single phase composition as a result of the alloying of the ferrite former and Fe has mainly a ferrite single phase (α single phase region) after the heating and the cooling. On the other hand, the unalloyed region in the base metal plate has mainly the α-γ transformed region after the heating and the cooling. Therefore, the α single phase region is substantially equivalent to the alloyed region. A ratio of the α single phase region to the base metal plate is preferably 1% or more in terms of an area ratio in a cross section in the thickness direction. When the ratio is less than 1%, the alloy region is not sufficiently formed and the sufficient accumulation degree of the {200} planes in the α phase is not sometimes obtained. In order to obtain a higher accumulation degree of the {200} planes in the α phase, the ratio is preferably 5% or more.
Further, in the α single phase region where the ferrite former is alloyed, since electric resistance is high, an effect of improving a core loss characteristic is obtained. As a desirable condition under which this effect is obtained, the ratio of the α single phase region to the metal plate in the thickness direction is 1% or more. When it is less than 1%, the accumulation degree of the {200} planes is not sufficiently high and it may be difficult to obtain an excellent core loss characteristic.
In order to obtain a more excellent core loss characteristic, the ratio of the α single phase region to the metal plate in the thickness direction is desirably not less than 5% nor more than 80%. When it is 5% or more, the accumulation degree of the {200} planes is remarkably high and the core loss characteristic accordingly improves. When it is 80% or less, the electric resistance of the α single phase region is still higher and the core loss is remarkably lower due to a synergistic effect with the effect of improving the accumulation degree of the {200} planes.
Here, the ratio of the α single phase region may be expressed by an expression (4), where T0 is an area of the cross section perpendicular to the surface of the Fe-based metal plate after the heating and the cooling and T is an area of the α single phase region after the heating and the cooling. Here, when Al is used as the ferrite former is, for example, the α single phase region is a region where the Al content is not less than 0.9 mass % nor more than 10 mass %. This range differs depending on the kind of the ferrite former and is a range shown in a Fe-based alloy phase diagram or the like.

ratio of α single phase region=(T/T0)×100  (4)

“Plane Accumulation Degrees in Fe-based Metal Plate”
The accumulation degree of the {200} planes in the α phase in the surface (rolled surface) of the Fe-based metal plate is 30% or more. When the accumulation degree of the {200} planes in the α phase is less than 30%, it may be not possible to obtain sufficiently high magnetic flux density. In order to obtain higher magnetic flux density, the accumulation degree of the {200} planes in the α phase is preferably 50% or more. However, when the accumulation degree of the {200} planes in the α phase is over 99%, the magnetic flux density saturates. Further, making the accumulation degree of the {200} planes in the α phase higher than 99% is difficult in view of manufacture. Therefore, the accumulation degree of the {200} planes in the α phase is preferably 99% or less, more preferably 95% or less.
The accumulation degree of the {222} planes in the α phase in the surface (rolled surface) of the Fe-based metal plate is 30% or less. When the accumulation degree of the {222} planes in the α phase is over 30%, it is not possible to obtain sufficiently high magnetic flux density. In order to obtain higher magnetic flux density, the accumulation degree of the {222} planes in the α phase is preferably 15% or less. However, when the accumulation degree of the {222} planes in the α phase is less than 0.01%, the magnetic flux density saturates. Further, making the accumulation degree of the {222} planes in the α phase less than 0.01% may be difficult in view of manufacture. Therefore, the accumulation degree of the {222} planes in the α phase is preferably 0.01% or more.
These plane accumulation degrees may be measured by X-ray diffraction using a MoKα ray. To be in more detail, in α phase crystals, integrated intensities of eleven orientation planes ({110}, {200}, {211}, {310}, {222}, {321}, {411}, {420}, {332}, {521}, and {442}) parallel to its surface is measured for each sample, each measurement value is divided by theoretical integrated intensity of the sample having random orientation, and thereafter, a ratio of the intensity of {200} or {222} is found in percentage.
At this time, the accumulation degree of the {200} planes in the α phase is expressed by an expression (1) and the accumulation degree of the {222} planes in the α phase is expressed by an expression (2), for example.

accumulation degree of {200}planes=[{i(200)/I(200)}/Σ{i(hkl)/I(hkl)}]×100  (1)

accumulation degree of {222}planes=[{i(222)/I(222)}/Σ{i(hkl)/I(hkl)}]×100  (2)

Here, i(hkl) is actually measured integrated intensity of {hkl} planes in the surface of the Fe-based metal plate or the base metal plate, and I(hkl) is theoretical integrated intensity of the {hkl} planes in the sample having random orientation. Incidentally, instead of the theoretical integrated intensity of the sample having the random orientation, results of actual measurement using the sample (actually measured values) may be used.
Incidentally, only making Al and Si contained in the steel plate for the purpose of reducing the core loss accompanying the increase in the electric resistance has difficulty in sufficiently reducing the core loss due to the influence of magnetostriction. When the α phase plane accumulation degree is within the aforesaid range, a remarkably good core loss can be obtained. This is thought to be because a difference in magnetostriction among grains is extremely small. This effect is distinguished especially when there are many columnar crystals extending in a direction perpendicular to the surface of the Fe-based metal plate.
“Thickness of Fe-Based Metal Plate”
The thickness of the Fe-based metal plate is preferably over 10 μm and 6 mm or less. When the thickness is 10 μm or less, very many Fe-based metal plates are used when they are stacked to form a magnetic core, which results in much gap between the Fe-based metal plates accompanying the stacking. As a result, high magnetic flux density may be difficult to obtain. Further, when the thickness is over 6 mm, it may be difficult to form a wide alloyed region and it is difficult to sufficiently improve the accumulation degree of the {200} planes in the α phase.
“State of Metal Layer after Heating and Cooling”
In accordance with the heating and the cooling, the whole metal layer may be diffused into the base metal plate or part of the metal layer may remain on a front surface and/or a rear surface of the base metal plate. Further, when part of the metal layer remains after the heating and the cooling, the remaining part may be removed by etching or the like. The metal layer remaining on the front surface and/or the rear surface of the base metal plate may enhance chemical stability of the surface layer portion of the Fe-based metal plate to improve corrosion resistance depending on its composition. When the metal layer is made to remain for the purpose of improving corrosion resistance, its thickness is preferably not more than 0.01 μm nor less than 500 μm. When the thickness is less than 0.01 μm, the metal layer may suffer a defect such as breakage, which is likely to make the core loss unstable. When the thickness is over 500 μm, the metal layer may suffer a defect such as exfoliation, which is likely to make corrosion resistance unstable.
“Transition of α Phase Plane Accumulation Degrees”
In heating the base metal plate and the metal layer, the accumulation degree of the {200} planes in the α phase is 25% or more and the accumulation degree of the {222} planes in the α phase is 40% or less in the alloy region when the A3 point is reached. When the accumulation degree of the {200} planes in the α phase is less than 25%, and when the accumulation degree of the {222} planes in the α phase is over 40%, it may be difficult to set the accumulation degree of the {222} planes in the α phase to 30% or less and the accumulation degree of the {200} planes in the α phase to 30% or more in the Fe-based metal plate. Further, the accumulation degree of the {200} planes in the α phase is preferably 50% or less and the accumulation degree of the {222} planes in the α phase is preferably 1% or more, in the alloy region when the A3 point is reached. When the accumulation degree of the {200} planes in the α phase is over 50%, and when the accumulation degree of the {222} planes in the α phase is less than 1%, the magnetic flux density of the Fe-based metal plate is likely to saturate. Further, in view of manufacture, it may be difficult to set the accumulation degree of the {200} planes in the α phase to more than 50% and to set the accumulation degree of the {222} planes in the α phase to less than 1%.
Further, in heating and cooling the base metal plate and the metal layer, it is preferable that the accumulation degree of the {200} planes in the α phase is 30% or more and the accumulation degree of the {222} planes in the α phase is 30% or less, in the alloy region when the cooling is started. When the accumulation degree of the {200} planes in the α phase is less than 30%, and when the accumulation degree of the {222} planes in the α phase is over 30%, it is likely to be difficult to set the accumulation degree of the {222} planes in the α phase to 30% or less and set the accumulation degree of the {200} planes in the α phase to 30% or more, in the Fe-based metal plate. Further, when the cooling is started, it is preferable that the accumulation degree of the {200} planes in the α phase is 99% or less and the accumulation degree of the {222} planes in the α phase is 0.01% or more, in the alloy region. When the accumulation degree of the {200} planes in the α phase is over 99%, and when the accumulation degree of the {222} planes in the α phase is less than 0.01%, the magnetic flux density of the Fe-based metal plate is likely to saturate. Further, in view of manufacture, it may be difficult to set the accumulation degree of the {200} planes in the α phase to over 99% and to set the accumulation degree of the {222} planes in the α phase to less than 0.01%.
Further, it is more preferable that the accumulation degree of the {200} planes in the α phase is 50% or more and the accumulation degree of the {222} planes in the α phase is 15% or less, in the alloy region when the cooling is started. Further, the accumulation degree of the {200} planes in the α phase is more preferably 95% or less in the alloy region when the cooling is started.
When an unalloyed region exists at the start of the cooling, the unalloyed region transforms from the γ phase to the α phase at the A3 point as described above. In the unalloyed region after the transformation, it is also preferable that the accumulation degree of the {200} planes in the α phase is not less than 30% nor more than 99%. When the accumulation degree of the {200} planes in the α phase is less than 30%, it is likely to be difficult to set the accumulation degree of the {222} planes in the α phase of the Fe-based metal plate to 30% or less. When the accumulation degree of the {200} planes in the α phase is over 99%, the magnetic flux density of the Fe-based metal plate is likely to saturate. Further, in view of manufacture, it may be difficult to set the accumulation degree of the {200} planes in the α phase to over 99%.
“Temperature Increasing Rate and Cooling Rate”
Heating up to the A3 point temperature and heating up to the temperature equal to or higher than the A3 point may be continuously performed, and temperature increasing rates thereof are preferably not less than 0.1° C./sec nor more than 500° C./sec. When the temperature increasing rate is within this range, grains whose planes parallel to the surface of the base metal plate are oriented in {100} are likely to be generated at the time of the recrystallization.
A keeping temperature after the temperature increase is preferably not lower than A3 point nor higher than 1300° C. When the temperature is kept at over 1300° C., the effect saturates. Further, the keeping time is not particularly limited, and the cooling may be started immediately after a predetermined temperature is reached. Further, when the temperature is kept for 36000 sec (ten hours), it is possible to fully diffuse the ferrite former into the metal layer.
A cooling rate at the time of the cooling to the temperature lower than A3 point is preferably not less than 0.1° C./sec nor more than 500° C./sec. The cooling with the temperature range facilitates enhancing the accumulation degree of the {200} planes in the α phase.
An atmosphere at the time of the temperature increase and an atmosphere at the time of the cooling are not particularly limited, and in order to suppress oxidization of the base metal plate and the metal layer, a non-oxidizing atmosphere is preferable. For example, an atmosphere of mixed gas of inert gas such as Ar gas or N2 gas and reducing gas such as H2 gas is preferable. Further, the temperature increase and/or the cooling may be performed under vacuum.
(First Embodiment)
Next, a first embodiment will be described. FIG. 2A to FIG. 2D are cross-sectional views showing a method of manufacturing a Fe-based metal plate according to the first embodiment of the present invention in order of processes.
In the first embodiment, as illustrated in FIG. 2A, metal layers 12 containing Al are first formed on a front surface and a rear surface of a base metal plate 11 composed of pure iron and having strain.
Next, the base metal plate 11 and the metal layers 12 are heated to the A3 point of the pure iron (911° C.) so that ferrite former in the metal layers 12 are diffused into the base metal plate 11, whereby alloy regions in an α phase are formed. The remainder of the base metal plate 11 is an unalloyed region in the α phase until an instant immediately before the A3 point is reached. In accordance with the heating, recrystallization occurs in the base metal plate 11. Further, because of the strain in the base metal plate 11, planes parallel to a surface (rolled surface) of the base metal plate 11, of grains generated by the recrystallization are likely to be oriented in {100}. Therefore, many grains whose planes parallel to the rolled surface are oriented in {100} are generated in the base metal plate 11.
Thereafter, the base metal plate 11 and the metal layers 12 are further heated up to a temperature equal to or higher than the A3 point of the pure iron. As a result, as illustrated in FIG. 2B, the unalloyed region 11a comprised of the α-γ transforming pure iron undergoes γ-transformation to become a γ phase, while the alloy regions 11b containing Al being the ferrite former are maintained in the α phase. Further, Al in the metal layers 12 further diffuses into the base metal plate 11, so that the alloy regions 11b in the α phase expand. Further, in the alloy regions 11b, since the grains 13 whose planes parallel to the rolled surface are oriented in {100} predominantly grow, an accumulation degree of {200} planes in the α phase increases and an accumulation degree of {222} planes in the α phase decreases, in the alloy regions 11b. 
Then, the base metal plate 11 and the metal layers 12 are kept at the temperature equal to or higher than the A3 point of the pure iron, and Al in the metal layers 12 further diffuses into the base metal plate 11, and as illustrated in FIG. 2C, the alloy regions 11b in the α phase expand. That is, in accordance with the diffusion of Al, part of the unalloyed region 11a in the γ phase changes to the alloy regions 11b in the α phase. At the time of the change, since the alloy regions 11b, which are adjacent to metal layer 12 sides of the regions undergoing the change, have been already oriented in {100}, the regions undergoing the change take over the crystal orientation of the alloy regions 11b to be oriented in {100}. As a result, the grains 13 whose planes parallel to the rolled surface are oriented in {100} further grow. Then, along with the growth of the grains 13, grains oriented in other directions vanish. For example, grains whose planes parallel to the rolled surface are oriented in {111} decrease. As a result, the accumulation degree of the {200} planes in the α phase further increases and the accumulation degree of the {222} planes in the α phase further decreases.
Subsequently, the base metal plate 11 is cooled to a temperature lower than the A3 point of the pure iron. As a result, as illustrated in FIG. 2D, the unalloyed region 11a undergoes α-transformation to become the α phase. At the time of the phase transformation as well, since the alloy regions 11b, which are adjacent to the metal layer 12 sides of the regions undergoing the phase transformation, have already been oriented in {100}, the regions undergoing the phase transformation take over the crystal orientation of the alloy regions 11b to be oriented in {100}. As a result, the grains 13 further grow. Then, along with the growth of the grains 13, the grains oriented in the other directions further vanish. As a result, the accumulation degree of the {200} planes in the α phase further increases and the accumulation degree of the {222} planes in the α phase further decreases. That is, a high accumulation degree of the {200} planes in the α phase is also obtained in the unalloyed region 11a. 
Thereafter, insulating films are formed on the surfaces of the metal layers 12. In this manner, the Fe-based metal plate may be manufactured. Incidentally, the metal layers 12 may be removed before the formation of the insulating films.
(Second Embodiment)
Next, a second embodiment will be described. FIG. 3 is a cross-sectional view showing a method of manufacturing a Fe-based metal plate according to the second embodiment of the present invention.
In the second embodiment, in the same manner as that of the first embodiment, the processes up to the heating of the base metal plate 11 and the metal layers 12 to a temperature of the A3 point of pure iron are performed (FIG. 2A to FIG. 2B). Then, the base metal plate 11 and the metal layers 12 are kept at a temperature equal to or higher than the A3 point. At this time, the temperature is kept for a longer time or the keeping temperature is made higher than in the first embodiment, and as illustrated in FIG. 3, Al in the metal layers 12 is all diffused into the base metal plate 11. Further, grains 13 are greatly gown, and almost all the grains oriented in directions other than {100} are made to vanish, so that the whole base metal plate 11 is turned into the α phase.
Thereafter, the cooling of the base metal plate 11 and the formation of the insulating films are performed in the same manner as that in the first embodiment. In this manner, the Fe-based metal plate may be manufactured.
(Third Embodiment)
Next, a third embodiment will be described. FIG. 4 is a cross-sectional view showing a method of manufacturing a Fe-based metal plate according to the third embodiment of the present invention.
In the third embodiment, in the same manner as that in the first embodiment, the processes up to the heating of the base metal plate 11 and the metal layers 12 to a temperature of the A3 point of pure iron are performed (FIG. 2A to FIG. 2B). Here, the metal layers 12 are formed thicker than in the first embodiment. Then, the base metal plate 11 and the metal layers 12 are kept at a temperature equal to or higher than the A3 point of the pure iron. At this time, the temperature is kept for a longer time or the keeping temperature is made higher than in the first embodiment, and as illustrated in FIG. 4, Al is diffused into the whole base metal plate 11. That is, the whole base metal plate 11 is turned into the alloy region 11b. 
Thereafter, the cooling of the base metal plate 11 and the formation of the insulating films are performed in the same manner as that in the first embodiment. In this manner, the Fe-based metal plate may be manufactured.
EXAMPLE
First Experiment
In a first experiment, correlations between 27 kinds of manufacturing conditions (condition No. 1-1 to condition No. 1-27) and an accumulation degree of {200} planes and an accumulation degree of {222} planes were studied.
Base metal plates used in the first experiment contained C: 0.0001 mass %, Si: 0.0001 mass %, Al: 0.0002 mass %, and inevitable impurities, with the balance being Fe. The base metal plates were fabricated in such manner that an ingot was produced by vacuum melting, followed by hot rolling and cold rolling. In the hot rolling, the ingot with a 230 mm thickness heated to 1000° C. was thinned to a 50 mm thickness, whereby a hot-rolled plate was obtained. Thereafter, plate materials different in thickness were cut out from the hot-rolled plate by machining, and the plate materials were subjected to the cold rolling with rolling reduction ratios listed in Table 1. Thicknesses of the obtained base metal plates (cold-rolled plates) are listed in Table 1.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope. In this measurement, a thin film sample with which a texture of a cross section perpendicular to a surface of each of the base metal plates could be observed was fabricated, and a region from the surface to a thickness-direction center of the base metal plate was observed. Then, texture photographs were taken at several places in this region, and the dislocation density was found from the number of dislocation lines. Average values of the obtained dislocation densities are listed in Table 1.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 20% to 26% range and the accumulation degree of the {222} planes in the α phase was an 18% to 24% range, in each of the base metal plates.
Thereafter, Al layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by an ion plating (IP) method or a hot dipping method, except in the condition No. 1-1. Thickness of each of the metal layers (total thickness on the both surfaces) is listed in Table 1. The metal layers whose thickness (total thickness on the both surfaces) was 0.01 μm to 0.4 μm were formed by the IP method, and the metal layers whose thickness (total thickness on the both surfaces) was 13 μm to 150 μm were formed by the hot dipping method. The total thickness on the both surfaces is a value obtained by summing the thickness measured on one surface and the thickness measured on the other surface.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions. A gold image furnace was used for the heat treatment, and the temperature increasing rate and the keeping time were variously controlled by program control. The temperature increase and the temperature keeping were performed in an atmosphere vacuumed to 10−3 Pa level. At the time of cooling at a cooling rate of 1° C./sec or lower, temperature control was performed in vacuum by furnace output control. At the time of cooling at a cooling rate of 10° C./sec or more, Ar gas was introduced and the cooling rate was controlled by the adjustment of its flow rate. In this manner, 27 kinds of Fe-based metal plates were manufactured.
Further, in the heat treatment, three samples were prepared per condition, and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment.
One of the samples (first sample) was heated from room temperature to the A3 point (911° C.) at each temperature increasing rate listed in Table 1, and was cooled to room temperature immediately at a cooling rate of 100° C./sec, except in the condition No. 1-2. In the condition No. 1-2, the sample was heated to 900° C. and was immediately cooled to room temperature at a cooling rate of 100° C./sec. Then, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured. Results of these are listed in Table 1.
Another sample (second sample) was heated from room temperature to 1000° C. at the same temperature increasing rate as that for the first sample, was kept at 1000° C. for each time listed in Table 1, and was cooled to room temperature at a cooling rate of 100° C./sec, except in No. 1-2. In the condition No. 1-2, the sample was heated to 900° C., was kept at 900° C. for the time listed in Table 1, and was cooled to room temperature at a cooling rate of 100° C./sec. Then, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured. Results of these are listed in Table 1.
The other one sample (third sample) was heated and was kept at 900° C. or 1000° C. similarly to the second sample, and thereafter was cooled to room temperature at each cooling rate listed in Table 1. Then, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured. Results of these are listed in Table 1. In the measurement of the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase in the third samples, when the whole Fe-based alloy plate was alloyed, a thickness-direction center region was an evaluation target, and when an unalloyed region existed in the Fe-based alloy plate, the unalloyed region was an evaluation target. Distances of these evaluation targets from the surface of the Fe-based alloy plate are listed in Table 1 (column of “distance”). In fabricating test pieces, portions above the evaluation targets were removed so that the evaluation targets were exposed.








TABLE 1








FIRST SAMPLE













BASE METAL PLATE

MEA-
ACCUMU-
ACCUMU-
















REDUC-
DISLOCA-

METAL LAYER

SURED
LATION
LATION


















CONDI-
TION
TION
THICK-

THICK-
HEATING
TEMPER-
DEGREE OF
DEGREE OF



TION
RATIO
DENSITY
NESS

NESS
RATE
ATURE
[200] PLANE
[222] PLANE



No.
(%)
(m/m3)
(μm)
ELEMTNT
(μm)
CCA)
(° C.)
(%)
(%)



















COMPARATIVE
1-1
97.6
2 × 1010
150
NONE
10
911
22
12

















EXAMPLE
1-2
97.6
2 × 1016
150
Al
20
10
900
23
12


EXAMPLE
1-3
95
6 × 1014
150
Al
20
10
911
27
11


OF
1-4
97.6
2 × 1016
150
Al
20
10
911
38
9


PRESENT
1-5
99.8
7 × 1018
150
Al
20
10
911
42
5.3


INVENTION
1-6
97.6
2 × 1015
8
Al
0.01
10
911
38
9



1-7
97.6
2 × 1016
30
Al
0.4
10
911
38
9



1-8
97.6
2 × 1010
350
Al
13
10
911
38
9



1-9
97.6
2 × 1016
500
Al
50
10
911
38
9



1-10
97.6
2 × 1016
750
Al
150
10
911
38
9



1-11
97.6
2 × 1016
150
Al
20
500
911
27
11



1-12
97.6
2 × 1010
150
Al
20
100
911
34
10



1-13
97.6
2 × 1016
150
Al
20
1
911
42
5.2



1-14
97.6
2 × 1016
150
Al
20
0.1
911
38
9



1-15
97.6
2 × 1015
160
Al
20
0.01
911
31
14



1-16
97.6
2 × 1016
150
Al
20
10
911
38
9



1-17
97.6
2 × 1015
150
Al
20
10
911
38
9



1-18
97.6
2 × 1015
150
Al
20
10
911
38
9



1-19
97.6
2 × 1010
150
Al
20
10
911
38
9



1-20
97.6
2 × 1015
150
Al
20
10
911
38
9



1-21
97.6
2 × 1015
150
Al
20
10
911
38
9



1-22
97.6
2 × 1015
150
Al
20
10
911
38
9



1-23
97.6
2 × 1016
150
Al
20
10
911
38
9



1-24
97.6
2 × 1016
150
Al
20
10
911
38
9



1-25
97.6
2 × 1016
150
Al
20
10
911
38
9



1-26
97.6
2 × 1015
150
Al
20
10
911
38
9



1-27
97.6
2 × 1015
150
Al
20
10
911
38
9













SECOND SAMPLE
THIRD SAMPLE




















ACCUMU-
ACCUMU-


ACCUMU-
ACCUMU-




KEEPING

LATION
LATION
COOL-

LATION
LATION



CONDI-
TEMPER-
KEEPING
DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



TION
ATURE
TIME
[200] PLANE
[222] PLANE
RATE
TANCE
[200] PLANE
[222] PLANE



No.
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
1-1
1000
10
13
13
100
75
13
13


EXAMPLE
1-2
900
10
24
12
100
78
24
12


EXAMPLE
1-3
1000
10
38
8
100
78
38
8


OF
1-4
1000
10
48
3.8
100
78
48
3.8


PRESENT
1-5
1000
10
72
0.2
100
78
72
0.2


INVENTION
1-6
1000
10
39
10
100
4
39
10



1-7
1000
10
40
8
100
16
40
8



1-8
1000
10
48
3.8
100
190
48
3.8



1-9
1000
10
48
3.8
100
250
48
3.8



1-10
1000
10
41
11
100
320
30
15



1-11
1000
10
39
8
100
78
39
8



1-12
1000
10
44
4.3
100
78
44
4.3



1-13
1000
10
55
2.1
100
78
55
11



1-14
1000
10
52
2.8
100
78
52
2.8



1-15
1000
10
40
8
100
78
40
8



1-16
1100
10
58
2.2
100
78
58
2.2



1-17
1250
10
63
1.3
100
78
63
1.3



1-18
1350
10
67
0.4
100
78
67
0.4



1-19
1000
0
42
8.5
100
78
42
8.5



1-20
1000
60
55
2.1
100
78
55
2.1



1-21
1000
600
60
1.7
100
78
60
1.7



1-22
1000
3600
63
1.3
100
78
63
1.3



1-23
1000
36000
64
1.2
100
78
64
1.2



1-24
1000
10
48
3.8
1000
78
39
8



1-25
1000
10
48
3.8
10
78
48
3.8



1-26
1000
10
48
3.8
1
78
48
3.8



1-27
1000
10
48
3.8
0.1
78
48
3.8









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured in the following manner. First, in-plane distribution of the Fe content and in-plane distribution of the Al content in the cross section perpendicular to the surface of the Fe-based metal plate were measured by an EPMA (Electron Probe Micro-Analysis) method. At this time, as for a field of view, its dimension in a direction parallel to the surface of the Fe-based metal plate (rolling direction) was set to 1 mm and its dimension in the thickness direction was set to a thickness of the Fe-based metal plate. Then, a region where the Fe content was 0.5 mass % or less and the Al content was 99.5 mass % or more was regarded as an alloy layer, and the alloying ratio was found from the aforesaid expression (3). Further, a region where the Al content was 0.9 mass % or more was regarded as an alloy region, and the ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 2.
Further, magnetic flux density B50 and saturation magnetic flux density Bs to a magnetizing force of 5000 A/m were measured. In the measurement of the magnetic flux density B50, a SST (Single Sheet Tester) was used, and a measurement frequency was set to 50 Hz. In the measurement of the saturation magnetic flux density Bs, a VSM (Vibrating Sample Magnetometer) was used and a magnetizing force of 0.8×106 A/m was applied. Then, a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Results of these are listed in Table 2.















TABLE 2








RATIO OF
ACCUMULATION
ACCUMULATION








α SINGLE
DEGREE OF
DEGREE OF






CONDITION
ALLOYING
PHASE
{200} PLANE
{222} PLANE
B50
Bs




No.
RATE (%)
(%)
(%)
(%)
(T)
(T)
B50/Bs























COMPARATIVE
1-1
—
0
13
13
1.70
2.16
0.79


EXAMPLE
1-2
73
0.9
24
12
1.55
1.95
0.79


EXAMPLE
1-3
87
35
38
8
1.71
1.95
0.88


OF
1-4
87
35
48
3.8
1.74
1.95
0.89


PRESENT
1-5
87
35
72
0.2
1.84
1.95
0.94


INVENTION
1-6
100
100
39
10
1.88
2.14
0.88



1-7
100
81
40
8
1.90
2.14
0.89



1-8
75
23
48
3.8
1.89
2.10
0.90



1-9
60
13
48
3.8
1.78
2.00
0.89



1-10
40
4
41
11
1.61
1.85
0.87



1-11
31
3
39
8
1.72
1.95
0.88



1-12
54
13
44
4.3
1.72
1.95
0.88



1-13
94
47
55
2.1
1.76
1.95
0.90



1-14
100
61
52
2.8
1.75
1.95
0.90



1-15
100
75
40
8
1.73
1.95
0.89



1-16
100
34
58
2.2
1.77
1.95
0.91



1-17
100
64
63
1.3
1.80
1.95
0.92



1-18
100
86
67
0.4
1.82
1.95
0.93



1-19
68
1.1
42
8.5
1.74
1.95
0.89



1-20
95
54
55
2.1
1.75
1.95
0.90



1-21
100
65
60
1.7
1.78
1.95
0.91



1-22
100
85
63
1.3
1.81
1.95
0.93



1-23
100
100
64
1.2
1.80
1.95
0.92



1-24
87
35
48
3.8
1.72
1.95
0.88



1-25
87
35
48
3.8
1.74
1.95
0.89



1-26
87
35
48
3.8
1.74
1.95
0.89



1-27
87
35
48
3.8
1.74
1.95
0.89









As listed in Table 1, in examples of the present invention (conditions No. 1-3 to No. 1-27), the accumulation degree of the {200} planes in the α phase was high at each of the stages of the heat treatment. Further, as listed in Table 2, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were high. As listed in Table 2, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was not less than 30% nor more than 99% and the accumulation degree of the {222} planes in the α phase was not less than 0.01% nor more than 30% were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.87 or more. That is, according to the examples of the present invention, an excellent magnetic property was obtained.
On the other hand, in the condition No. 1-1 being a comparative example, since the metal layer was not formed, a high accumulation degree of the {200} planes in the α phase was not obtained and a good magnetic property was not obtained even though high-density dislocation existed in the base metal plate. In the condition No. 1-2 being a comparative example, since the heating temperature was lower than the A3 point (911° C.), improvement in the accumulation degree of the {200} planes in the α phase owing to the γ-α transformation was not caused, and a good magnetic property was not obtained.
Second Experiment
In a second experiment, six kinds of base metal plates different in composition were used, and various kinds of materials were used as the metal layers, and correlations between 73 kinds of conditions (condition No. 2-1 to condition No. 2-73) and an accumulation degree of {200} planes and an accumulation degree of {222} planes were studied.
Components contained in six kinds of the base metal plates used in the second experiment are listed in Table 3. The balance of the base metal plates was Fe and inevitable impurities. Table 3 also lists actually measured values of A3 points of the base metal plates. The base metal plates were fabricated in such a manner that an ingot was produced by vacuum melting, followed by hot rolling and cold rolling. In the hot rolling, the ingot with a 230 mm thickness heated to 1000° C. was thinned to a 50 mm thickness, whereby a hot-rolled plate was obtained. Thereafter, plate materials different in thickness were cut out from the hot-rolled plate by machining, and the plate materials were subjected to the cold rolling with rolling reduction ratios listed in Table 4, subjected to shot blasting, or subjected to the both. In the shot blasting, iron beads each with a 1 mm to 3 mm diameter were made to continuously collide with both surfaces of the base metal plates for ten seconds each. Whether the shot blasting was performed or not and the thickness of each of the obtained base metal plates (cold-rolled plates) are listed in Table 4 and Table 5.









TABLE 3







COMPOSITION OF
COMPONENT ELEMENT (mass %)
A3 POINT

















BASE METAL PLATE
C
Si
Mn
Al
P
N
S
O
OTHERS
(° C.)




















A
0.0003
0.05
0.15
0.0005
0.0001
0.0002
<0.0004
0.0002
Ti: 0.03
910


B
0.0002
0.1
0.12
0.0002
0.0001
0.0003
<0.0004
0.0001
Zr: 0.02
911


C
0.0002
0.3
0.08
0.05
0.0001
0.0003
<0.0004
0.0001

916


D
0.0001
0.4
0.12
0.15
0.0001
0.0002
<0.0004
0.0001

922


E
0.0001
0.5
1.0
0.21
0.0001
0.0003
<0.0004
0.0001
Cr: 2.0
914


F
0.0001
0.01
1.7
0.01
0.0001
0.0002
<0.0004
0.0001

872









Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope in the same manner as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 50 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 4 and Table 5.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 19% to 27% range and the accumulation degree of the {222} planes in the α phase was within a 18% to 25% range in each of the base metal plates.
Thereafter, metal layers were formed on a front Surface and a rear surface of each of the base metal plates by an IP method, a hot dipping method, a sputtering method, or a vapor deposition method, except in the conditions No. 2-1, No. 2-13, No. 2-25, No. 2-37, No. 2-43, No. 2-49, No. 2-55, No. 2-61, and No. 2-67. Thickness of each of the metal layers (total thickness on the both surfaces) is listed in Table 4 and Table 5. Si layers were formed by the IP method, Sn layers were formed by the hot dipping method, and Ti layers were formed by the sputtering method. Further, Ga layers were formed by the vapor deposition method, Ge layers were formed by the vapor deposition method, No layers were formed by the sputtering method, V layers were formed by the sputtering method, Cr layers were formed by the sputtering method, and As layers were formed by the vapor deposition method.
Subsequently, heat treatment was applied on the base metal plates, on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 4 and Table 5.









TABLE 4








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSITY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
2-1
A
WITHOUT
97.2
1 × 1016
250
NONE















EXAMPLE
2-2
A
WITHOUT
97.2
1 × 1016
250
Si
33


EXAMPLE
2-3
A
WITHOUT
971
1 × 1016
250
Si
33


OF
2-4
A
WITHOUT
972
1 × 1016
250
Si
33


PRESENT
2-5
A
WITHOUT
97.2
1 × 1016
250
Si
33


INVENTION
2-6
A
WITHOUT
97.2
1 × 1016
250
Si
33



2-7
B
WITH
0
1 × 1014
350
Si
38



2-8
B
WITH
49
8 × 1014
350
Si
38



2-9
B
WITH
50
1 × 1015
350
Si
38



2-10
B
WITH
70
6 × 1015
350
Si
38



2-11
B
WITH
90
5 × 1015
350
Si
38



2-12
B
WITH
97
1 × 1017
350
Si
38














COMPARATIVE
2-13
C
WITHOUT
98.2
3 × 1016
326
NONE















EXAMPLE
2-14
C
WITHOUT
98.2
3 × 1016
326
Sn
17


EXAMPLE
2-15
C
WITHOUT
98.2
3 × 1016
326
Sn
17


OF
2-16
C
WITHOUT
98.2
3 × 1016
326
Sn
17


PRESENT
2-17
C
WITHOUT
98.2
3 × 1016
326
Sn
17


INVENTION
2-18
C
WITHOUT
98.2
3 × 1016
326
Sn
17



2-19
D
WITH
0
1 × 1014
500
Sn
23



2-20
D
WITH
49
7 × 1014
500
Sn
23



2-21
D
WITH
50
1 × 1015
500
Sn
23



2-22
D
WITH
70
5 × 1015
500
Sn
23



2-23
D
WITH
90
7 × 1016
500
Sn
23



2-24
D
WITH
97
1 × 1017
500
Sn
23














COMPARATIVE
2-25
E
WITHOUT
97.1
2 × 1016
100
NONE















EXAMPLE
2-26
E
WITHOUT
97.1
2 × 1016
100
Ti
8


EXAMPLE
2-27
E
WITHOUT
97.1
2 × 1016
100
Ti
8


OF
2-28
E
WITHOUT
97.1
2 × 1016
100
Ti
8


PRESENT
2-29
E
WITHOUT
97.1
2 × 1016
100
Ti
8


INVENTION
2-30
E
WITHOUT
97.1
2 × 1016
100
Ti
8



2-31
F
WITH
0
1 × 1014
700
Ti
29



2-32
F
WITH
49
8 × 1014
700
Ti
29



2-33
F
WITH
50
1 × 1015
700
Ti
29



2-34
F
WITH
70
7 × 1015
700
Ti
29



2-35
F
WITH
90
5 × 1016
700
Ti
29



2-36
F
WITH
97
1 × 1017
700
Ti
29













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
[200] PLANE
[222] PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
2-1
20
910
18
14
1000
20


EXAMPLE
2-2
20
900
21
13
900
20


EXAMPLE
2-3
20
910
36
8
1000
20


OF
2-4
20
910
36
8
1100
20


PRESENT
2-5
20
910
35
8
1250
20


INVENTION
2-6
20
910
35
8
1350
20



2-7
10
911
25
13
1200
120



2-8
10
911
26
11
1200
120



2-9
10
911
27
10
1200
120



2-10
10
911
39
7
1200
120



2-11
10
911
41
5.1
1200
120



2-12
10
911
48
4.2
1200
120


COMPARATIVE
2-13
8
916
19
12
1000
40


EXAMPLE
2-14
8
900
24
12
900
40


EXAMPLE
2-15
8
916
45
5.7
1000
40


OF
2-16
8
916
45
5.7
1100
40


PRESENT
2-17
8
916
45
5.7
1250
40


INVENTION
2-18
8
916
45
5.7
1350
40



2-19
1
922
25
13
1050
1800



2-20
1
922
26
11
1050
1800



2-21
1
922
27
10
1050
1800



2-22
1
922
37
8
1050
1800



2-23
1
922
42
5.2
1050
1800



2-24
1
922
46
5.6
1050
1800


COMPARATIVE
2-25
10
914
19
12
1000
40


EXAMPLE
2-26
10
900
23
12
900
40


EXAMPLE
2-27
10
914
45
5.7
1000
40


OF
2-28
10
914
45
5.7
1100
40


PRESENT
2-29
10
914
45
5.7
1250
40


INVENTION
2-30
10
914
45
5.7
1350
40



2-31
0.1
872
25
12
950
350



2-32
0.1
872
25
11
950
360



2-33
0.1
872
27
10
950
360



2-34
0.1
872
38
7
950
380



2-35
0.1
872
41
8
950
360



2-36
0.1
872
43
5.3
950
360













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
[200] PLANE
[222] PLANE
RATE
TANCE
[200] PLANE
[222] PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
2-1
13
13
200
125
13
13


EXAMPLE
2-2
23
11
200
132
23
11


EXAMPLE
2-3
49
3.9
200
132
49
3.9


OF
2-4
60
1.9
200
132
60
1.9


PRESENT
2-5
75
0.5
200
132
75
0.5


INVENTION
2-6
74
0.6
200
132
74
0.6



2-7
30
12
80
185
30
12



2-8
31
10
80
185
31
10



2-9
41
5.8
80
185
41
5.8



2-10
72
0.9
80
185
72
0.9



2-11
75
0.8
80
185
75
0.8



2-12
92
0.1
80
185
92
0.1


COMPARATIVE
2-13
13
13
50
163
13
13


EXAMPLE
2-14
25
12
50
175
25
12


EXAMPLE
2-15
53
2.5
50
175
53
2.5


OF
2-16
73
0.6
50
175
73
0.6


PRESENT
2-17
95
0.1
50
175
95
0.1


INVENTION
2-18
74
0.8
50
175
74
0.8



2-19
30
10
100
265
30
10



2-20
35
9
100
265
35
9



2-21
43
5.4
100
265
43
5.4



2-22
69
1.5
100
265
69
1.5



2-23
73
0.8
100
265
73
0.8



2-24
77
0.5
100
265
77
0.6


COMPARATIVE
2-25
13
13
10
50
13
13


EXAMPLE
2-26
25
12
10
54
25
12


EXAMPLE
2-27
53
2.5
10
54
53
2.5


OF
2-28
73
0.6
10
54
73
0.6


PRESENT
2-29
95
0.1
10
54
95
0.1


INVENTION
2-30
74
0.8
10
54
74
0.8



2-31
31
9
80
280
30
9



2-32
32
10
80
280
30
12



2-33
41
6
80
280
36
9



2-34
52
2.8
80
280
46
6



2-35
58
2.1
80
280
50
2.9



2-36
63
1.6
80
280
54
2.9


















TABLE 5








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSITY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
2-37
A
WITH
70
8 × 1015
350
NONE















EXAMPLE
2-38
A
WITH
70
8 × 1015
350
Ga
18


EXAMPLE
2-39
A
WITH
70
8 × 1015
350
Ga
18


OF
2-40
A
WITH
70
8 × 1015
350
Ga
18


PRESENT
2-41
A
WITH
70
8 × 1015
350
Ga
18


INVENTION
2-42
A
WITH
70
8 × 1015
350
Ga
18














COMPARATIVE
2-43
B
WITH
78
7 × 1018
240
NONE















EXAMPLE
2-44
B
WITH
78
7 × 1018
240
Ge
11


EXAMPLE
2-45
B
WITH
78
7 × 1018
240
Ge
11


OF
2-46
B
WITH
78
7 × 1018
240
Ge
11


PRESENT
2-47
B
WITH
78
7 × 1018
240
Ge
11


INVENTION
2-48
B
WITH
78
7 × 1018
240
Ge
11














COMPARATIVE
2-49
C
WITH
50
1 × 1017
500
NONE















EXAMPLE
2-50
C
WITH
50
1 × 1017
500
Mo
8


EXAMPLE
2-51
C
WITH
50
1 × 1017
500
Mo
8


OF
2-52
C
WITH
50
1 × 1017
500
Mo
8


PRESENT
2-53
C
WITH
50
1 × 1017
500
Mo
8


INVENTION
2-54
C
WITH
50
1 × 1017
500
Mo
8














COMPARATIVE
2-55
D
WITH
90
3 × 1016
150
NONE















EXAMPLE
2-56
D
WITH
90
3 × 1016
150
V
6


EXAMPLE
2-57
D
WITH
90
3 × 1016
150
V
6


OF
2-58
D
WITH
90
3 × 1016
150
V
6


PRESENT
2-59
D
WITH
90
3 × 1016
150
V
6


INVENTION
2-60
D
WITH
90
3 × 1016
150
V
6














COMPARATIVE
2-61
E
WITH
95
6 × 1016
100
NONE















EXAMPLE
2-62
E
WITH
95
6 × 1016
100
Cr
5


EXAMPLE
2-63
E
WITH
95
6 × 1016
100
Cr
5


OF
2-64
E
WITH
95
6 × 1016
100
Cr
5


PRESENT
2-65
E
WITH
95
6 × 1016
100
Cr
5


INVENTION
2-66
E
WITH
95
6 × 1016
100
Cr
5














COMPARATIVE
2-67
F
WITH
80
2 × 1015
200
NONE















EXAMPLE
2-68
F
WITH
80
2 × 1015
200
As
11


EXAMPLE
2-69
F
WITH
80
2 × 1015
200
As
11


OF
2-70
F
WITH
80
2 × 1015
200
As
11


PRESENT
2-71
F
WITH
80
2 × 1015
200
AS
11


INVENTION
2-72
F
WITH
80
2 × 1015
200
As
11



2-73
F
WITH
80
2 × 1015
200
As
11













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
{200} PLANE
{222} PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
2-37
50
910
19
13
1000
120


EXAMPLE
2-38
50
900
21
13
900
120


EXAMPLE
2-39
50
910
34
8
1000
120


OF
2-40
50
910
34
8
1100
120


PRESENT
2-41
50
910
34
8
1250
120


INVENTION
2-42
50
910
34
8
1350
120


COMPARATIVE
2-43
30
911
19
13
1000
25


EXAMPLE
2-44
30
900
23
11
900
25


EXAMPLE
2-45
30
911
41
6.3
1000
25


OF
2-46
30
911
41
6.3
1100
25


PRESENT
2-47
30
911
41
6.3
1250
25


INVENTION
2-48
30
911
41
6.3
1350
25


COMPARATIVE
2-49
10
916
18
15
1000
360


EXAMPLE
2-50
10
900
24
12
900
360


EXAMPLE
2-51
10
916
45
5.2
1000
360


OF
2-52
10
916
45
5.2
1100
360


PRESENT
2-53
10
916
45
5.2
1250
350


INVENTION
2-54
10
916
45
5.2
1350
350


COMPARATIVE
2-55
1
922
17
14
1000
1800


EXAMPLE
2-56
1
900
23
11
900
1800


EXAMPLE
2-57
1
922
42
6.2
1000
1800


OF
2-58
1
922
42
6.2
1100
1800


PRESENT
2-59
1
922
42
6.2
1250
1800


INVENTION
2-60
1
922
42
6.2
1350
1800


COMPARATIVE
2-61
5
914
16
14
1000
720


EXAMPLE
2-62
5
900
23
11
900
720


EXAMPLE
2-63
5
914
48
5.6
1000
720


OF
2-64
5
914
48
5.6
1100
720


PRESENT
2-65
5
914
48
5.6
1250
720


INVENTION
2-66
5
814
48
5.6
1350
720


COMPARATIVE
2-67
0.1
872
14
12
950
30


EXAMPLE
2-68
0.1
850
22
13
850
30


EXAMPLE
2-69
0.1
872
32
9.4
950
30


OF
2-70
0.1
872
32
9.4
1050
30


PRESENT
2-71
0.1
872
32
9.4
1150
30


INVENTION
2-72
0.1
872
32
9.4
1250
30



2-73
0.1
872
32
9.4
1350
30













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
{200} PLANE
{222} PLANE
RATE
TANCE
{200} PLANE
{222} PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
2-37
13
13
50
175
13
13


EXAMPLE
2-38
22
12
50
176
22
12


EXAMPLE
2-39
45
4.8
50
176
45
4.8


OF
2-40
52
2.8
50
176
52
2.8


PRESENT
2-41
68
1.9
50
176
68
1.9


INVENTION
2-42
65
2.1
50
176
65
0.6


COMPARATIVE
2-43
13
13
100
120
13
13


EXAMPLE
2-44
23
11
100
125
23
11


EXAMPLE
2-45
51
2.9
100
125
51
2.9


OF
2-46
63
2.2
100
125
63
2.2


PRESENT
2-47
78
0.8
100
125
78
0.8


INVENTION
2-48
69
1.8
100
125
69
1.8


COMPARATIVE
2-49
13
13
150
250
13
13


EXAMPLE
2-50
25
11
150
251
25
11


EXAMPLE
2-51
55
2.4
150
251
55
2.4


OF
2-52
68
1.8
150
251
68
1.8


PRESENT
2-53
84
0.6
150
251
84
0.6


INVENTION
2-54
73
1.4
150
251
73
1.4


COMPARATIVE
2-55
13
13
80
75
13
13


EXAMPLE
2-56
26
10
80
75
26
10


EXAMPLE
2-57
51
2.7
80
75
51
2.7


OF
2-58
59
2.3
80
75
50
2.3


PRESENT
2-59
71
1.2
80
75
71
1.2


INVENTION
2-60
60
2.4
80
75
00
2.4


COMPARATIVE
2-61
13
13
10
50
13
13


EXAMPLE
2-62
25
10
10
53
25
10


EXAMPLE
2-63
59
2.2
10
53
59
2.2


OF
2-64
65
1.6
10
53
65
1.0


PRESENT
2-65
78
0.9
10
53
78
0.9


INVENTION
2-66
70
1.6
10
53
70
1.6


COMPARATIVE
2-67
13
13
1
100
13
13


EXAMPLE
2-68
23
11
1
101
23
11


EXAMPLE
2-69
39
8.4
1
101
39
8.4


OF
2-70
44
5.4
1
101
44
5.4


PRESENT
2-71
56
2.6
1
101
56
2.6


INVENTION
2-72
73
1.5
1
101
73
1.5



2-73
70
1.6
1
101
70
1.6









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each Fe-based metal plate were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5% or more was regarded as an alloy layer. Further, in finding the ratio of the α single phase region, an alloy region was decided as described in the following. In the conditions No. 2-2 to No. 2-12 using Si as the metal layers, a region where the Si content was 1.9 mass % or more was regarded as the alloy region. In the conditions No. 2-14 to No. 2-24 using Sn as the metal layers, a region where the Sn content was 3.0 mass % or more was regarded as the alloy region. In the conditions No. 2-26 to No. 2-36 using Ti as the metal layers, a region where the Ti content was 1.2 mass % or more was regarded as the alloy region. In the conditions No. 2-38 to No. 2-42 using Ga as the metal layers, a region where the Ga content was 4.1 mass % or more was regarded as the alloy region. In the conditions No. 2-44 to No. 2-48 using Ge as the metal layers, a region where the Ge content was 6.4 mass % or more was regarded as the alloy region. In the conditions No. 2-50 to No. 2-54 using Mo as the metal layers, a region where the Mo content was 3.8 mass % or more was regarded as the alloy region. In the conditions No. 2-56 to No. 2-60 using V as the metal layers, a region where the V content was 1.8 mass % or more was regarded as the alloy region. In the conditions No. 2-62 to No. 2-66 using Cr as the metal layers, a region where the Cr content was 13.0 mass % or more was regarded as the alloy region. In the conditions No. 2-68 to No. 2-73 using As as the metal layers, a region where the As content was 3.4 mass % or more was regarded as the alloy region. Results of these are listed in Table 6 and Table 7.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Results of these are listed in Table 6 and Table 7.















TABLE 6








RATIO OF
ACCUMULATION
ACCUMULATION







ALLOYING
α SINGLE
DEGREE OF
DEGREE OF






CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs




No.
(%)
(%)
(%)
(%)
(T)
(T)
B50/Bs























COMPARATIVE
2-1
—
0
13
13
1.70
2.16
0.79


EXAMPLE
2-2
 69
0.9
23
11
1.55
1.96
0.79


EXAMPLE
2-3
100
8.4
49
3.9
1.75
1.96
0.89


OF
2-4
100
16
60
1.9
1.77
1.96
0.90


PRESENT
2-5
100
36
75
0.5
1.83
1.96
0.93


INVENTION
2-8
100
47
74
0.6
1.82
1.96
0.93



2-7
100
38
30
12
1.71
1.99
0.86



2-8
100
38
31
10
1.73
1.99
0.87



2-9
100
37
41
5.8
1.77
1.99
0.89



2-10
100
38
72
0.9
1.83
1.99
0.92



2-11
100
37
75
0.8
1.85
1.99
0.93



2-12
100
38
92
0.1
1.91
1.99
0.96


COMPARATIVE
2-13
—
0
13
13
1.67
2.16
0.77


EXAMPLE
2-14
 75
0.4
25
12
1.53
1.94
0.79


EXAMPLE
2-15
100
4.7
53
2.5
1.75
1.94
0.90


OF
2-16
100
11
73
0.6
1.77
1.94
0.91


PRESENT
2-17
100
26
95
0.1
1.90
1.94
0.98


INVENTION
2-18
100
31
74
0.8
1.77
1.94
0.91



2-19
100
19
30
10
1.69
1.96
0.86



2-20
100
19
35
9
1.71
1.96
0.87



2-21
100
18
43
5.4
1.74
1.96
0.89



2-22
100
20
69
1.5
1.78
1.96
0.91



2-23
100
20
73
0.8
1.80
1.96
0.92



2-24
100
19
77
0.6
1.82
1.96
0.93


COMPARATIVE
2-25
—
0
13
13
1.68
2.16
0.78


EXAMPLE
2-26
 75
0.4
25
12
1.55
1.96
0.79


EXAMPLE
2-27
100
4.7
53
2.5
1.76
1.96
0.90


OF
2-28
100
11
73
0.6
1.81
1.96
0.92


PRESENT
2-29
100
26
97
0.1
1.91
1.96
0.97


INVENTION
2-30
100
31
74
0.8
1.82
1.96
0.93



2-31
100
19
31
9
1.74
2.05
0.85



2-32
100
19
32
10
1.76
2.05
0.86



2-33
100
18
41
6
1.80
2.05
0.88



2-34
100
20
52
2.8
1.85
2.05
0.90



2-35
100
20
58
2.1
1.87
2.05
0.91



2-36
100
19
63
1.6
1.89
2.05
0.92
























TABLE 7









ACCUMULATION
ACCUMULATION








RATIO OF
DEGREE OF
DEGREE OF






CONDITION
ALLOYING
α SINGLE
{200} PLANE
{222} PLANE
B50
Bs




No.
RATE (%)
PHASE (%)
(%)
(%)
(T)
(T)
B50/Bs























COMPARATIVE
2-37
—
0
13
13
1.70
2.16
0.79


EXAMPLE
2-38
 87
0.8
22
12
1.56
1.98
0.79


EXAMPLE
2-39
100
3.6
45
4.8
1.76
1.98
0.89


OF
2-40
100
8.9
52
2.8
1.78
1.98
0.90


PRESENT
2-41
100
19.5
68
1.9
1.84
1.98
0.93


INVENTION
2-42
100
27.3
65
0.6
1.84
1.98
0.93


COMPARATIVE
2-43
—
0
13
13
1.70
2.16
0.79


EXAMPLE
2-44
 68
0.9
22
12
1.59
2.01
0.79


EXAMPLE
2-45
 95
7.5
51
2.9
1.79
2.01
0.89


OF
2-46
100
18.4
63
2.2
1.81
2.01
0.90


PRESENT
2-47
100
31
78
0.8
1.87
2.01
0.93


INVENTION
2-48
100
44
69
1.8
1.87
2.01
0.93


COMPARATIVE
2-49
—
0
13
13
1.68
2.16
0.78


EXAMPLE
2-50
 47
0.3
25
11
1.63
2.06
0.79


EXAMPLE
2-51
 98
2.8
55
2.4
1.85
2.06
0.90


OF
2-52
100
5.9
68
1.8
1.88
2.06
0.91


PRESENT
2-53
100
8.4
84
0.6
1.92
2.06
0.93


INVENTION
2-54
100
11.8
73
1.4
1.89
2.06
0.92


COMPARATIVE
2-55
—
0
13
13
1.68
2.16
0.78


EXAMPLE
2-56
 78
0.8
26
10
1.63
2.01
0.81


EXAMPLE
2-57
100
3.5
51
2.7
1.81
2.01
0.90


OF
2-58
100
6.9
59
2.3
1.83
2.01
0.91


PRESENT
2-59
100
9.5
71
1.2
1.84
2.01
0.92


INVENTION
2-60
100
12.1
60
2.4
1.83
2.01
0.91


COMPARATIVE
2-61
—
0
13
13
1.68
2.16
0.78


EXAMPLE
2-62
 37
0.9
25
10
1.53
1.98
0.78


EXAMPLE
2-63
100
8.6
59
2.2
1.76
1.96
0.90


OF
2-64
100
14.2
65
1.6
1.79
1.96
0.91


PRESENT
2-65
100
25.7
78
0.9
1.82
1.96
0.93


INVENTION
2-66
100
32.8
70
1.6
1.80
1.96
0.92


COMPARATIVE
2-67
—
0
13
13
1.67
2.16
0.77


EXAMPLE
2-68
 45
0.8
23
11
1.54
1.98
0.78


EXAMPLE
2-69
 88
6.7
39
8.4
1.72
1.98
0.87


OF
2-70
100
13.8
44
5.4
1.74
1.98
0.88


PRESENT
2-71
100
28.4
56
2.6
1.80
1.98
0.91


INVENTION
2-72
100
39.3
73
1.5
1.83
1.98
0.92



2-73
100
47.5
70
1.6
1.79
1.98
0.90









As listed in Table 4 and Table 5, in examples of the present invention (conditions No. 2-3 to No. 2-12, No. 2-15 to No. 2-24, No. 2-27 to No. 2-36, No. 2-39 to No. 2-42, No. 2-45 to No. 2-48, No. 2-51 to No. 2-54, No. 2-57 to No. 2-60, No. 2-63 to No. 2-66, and No. 2-69 to No. 2-73), the accumulation degree of the {200} planes in the α phase was high at each of the stages of the heat treatment. Further, as listed in Table 6 and Table 7, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were high. As listed in Table 6 and Table 7, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was not less than 30% nor more than 99% and the accumulation degree of the {222} planes in the α phase was not less than 0.01% nor more than 30% were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more. That is, according to the examples of the present invention, an excellent magnetic property was obtained.
On the other hand, in the conditions No. 2-1, No. 2-13, No. 2-25, No. 2-37, No. 2-43, No. 2-49, No. 2-55, No. 2-61, and No. 2-67 being comparative examples, since the metal layer was not formed, a high accumulation degree of the {200} planes in the α phase was not obtained and a good magnetic property was not obtained even though high-density dislocation existed in the base metal plate. In the conditions No. 2-2, No. 2-14, No. 2-26, No. 2-38, No. 2-44, No. 2-50, No. 2-56, No. 2-62, and No. 2-68 being comparative examples, since the heating temperature was lower than the A3 point, improvement in the accumulation degree of the {200} planes in the α phase owing to the γ-α transformation was not caused, and a good magnetic property was not obtained.
Third Experiment
In a third experiment, six kinds of base metal plates different in composition were used, and various kinds of materials were used as the metal layers, and correlations between 42 kinds of conditions (condition No. 3-1 to condition No. 3-42) and an accumulation degree of {200} planes and an accumulation degree of {222} planes were studied.
Components contained in six kinds of the base metal plates used in the third experiment are listed in Table 8. The balance of the base metal plates was Fe and inevitable impurities. Table 8 also lists actually measured values of A3 points of the base metal plates. The base metal plates were fabricated in such a manner that an ingot was produced by vacuum melting, followed by hot rolling and cold rolling. In the hot rolling, the ingot with a 230 mm thickness heated to 1000° C. was thinned to a 50 mm thickness, whereby a hot-rolled plate was obtained. Thereafter, plate materials different in thickness were cut out from the hot-rolled plate by machining, and the plate materials were subjected to the cold rolling with rolling reduction ratios listed in Table 9, and a shear strain was generated. To generate the shear strain, upper and lower reduction rolls are rotated at different speeds at the time of the cold rolling. Some of the base metal plates were also subjected to shot blasting as in the second embodiment. Whether the shot blasting was performed or not, the shear strain, and the thickness of each of the obtained base metal plates (cold-rolled plates) are listed in Table 9. Note that the shear strain was calculated from diameters of the reduction rolls and a difference in speed between the reduction rolls.









TABLE 8







COMPOSITION OF
COMPONENT ELEMENT (mass %)
A3 POINT

















BASE METAL PLATE
C
Si
Mn
Al
P
N
S
O
OTHERS
(° C.)




















G
0.001
0.14
0.23
0.001
0.0001
0.0002
<0.0004
0.0002
Cu: 0.01
898


H
0.0002
0.08
0.06
0.0015
0.0021
0.0004
<0.0004
0.0003
Ni: 0.15
887


I
0.03
0.09
0.09
0.0008
0.0025
0.0003
<0.0004
0.0007
Cu: 0.15
905


J
0.0001
0.07
0.12
0.15
0.0004
0.0002
<0.0004
0.0005
Ni: 0.5
868


K
0.0003
0.85
0.07
0.53
0.0003
0.0003
<0.0004
0.0001

921


L
0.0002
0.03
0.08
0.7
0.0003
0.0002
<0.0004
0.0001

925









Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 19% to 27% range and the accumulation degree of the {222}planes in the α phase was within a 18% to 25% range in each of the base metal plates.
Thereafter, metal layers were formed on a front surface and a rear surface of each of the base metal plates by an IP method, a hot dipping method, a sputtering method, or a rolling clad method, except in the conditions No. 3-13, No. 3-19, No. 3-25, No. 3-31, and No. 3-37. Thickness of each of the metal layers (total thickness on the both surfaces) is listed in Table 9. Al layers with a 0.7 μm thickness were formed by the IP method, Al layers with a 7 μm to 68 μm thickness were formed by the hot dipping method, and Al layers with a 205 μm or 410 μm thickness were formed by the rolling clad method. Sb layers and W layers were formed by the sputtering method, and Zn layers, Al—Si alloy layers, and Sn—Zn alloy layers were formed by the hot dipping method.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 9.









TABLE 9








BASE METAL PLATE












REDUCTION

METAL LAYER















CONDITION
COMPO-
RATE
SHEAR
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
STRAIN
(μm)
ELEMENT
(μm)





COMPARATIVE
3-1
G
WITHOUT
70
0
350
Al
24


EXAMPLE
3-2
G
WITHOUT
70
0.1
350
Al
24


EXAMPLE
3-3
G
WITHOUT
70
0.2
350
Al
24


OF
3-4
G
WITHOUT
70
0.4
350
Al
24


PRESENT
3-5
G
WITHOUT
70
0.6
350
Al
24


INVENTION
3-6
G
WITHOUT
70
0.8
350
Al
24



3-7
G
WITH
55
0.4
10
Al
0.7



3-8
G
WITH
55
0.4
100
Al
7



3-9
G
WITH
55
0.4
500
Al
34



3-10
G
WITH
55
0.4
1000
Al
68



3-11
G
WITH
55
0.4
3000
Al
205



3-12
G
WITH
55
0.4
6000
Al
410














COMPARATIVE
3-13
H
WITHOUT
75
0.5
200
NONE















EXAMPLE
3-14
H
WITHOUT
75
0.5
200
Sb
6


EXAMPLE
3-15
H
WITHOUT
75
0.5
200
Sb
6


OF
3-16
H
WITHOUT
75
0.5
200
Sb
6


PRESENT
3-17
H
WITHOUT
75
0.5
200
Sb
6


INVENTION
3-18
H
WITHOUT
75
0.5
200
Sb
6














COMPARATIVE
3-19
I
WITHOUT
85
0.6
150
NONE















EXAMPLE
3-20
I
WITHOUT
85
0.6
150
W
2


EXAMPLE
3-21
I
WITHOUT
85
0.6
150
W
2


OF
3-22
I
WITHOUT
85
0.6
150
W
2


PRESENT
3-23
I
WITHOUT
85
0.6
150
W
2


INVENTION
3-24
I
WITHOUT
85
0.6
150
W
2














COMPARATIVE
3-25
J
WITH
70
0.2
700
NONE















EXAMPLE
3-26
J
WITH
70
0.2
700
Zn
44


EXAMPLE
3-27
J
WITH
70
0.2
700
Zn
44


OF
3-28
J
WITH
70
0.2
700
Zn
44


PRESENT
3-29
J
WITH
70
0.2
700
Zn
44


INVENTION
3-30
J
WITH
70
0.2
700
Zn
44














COMPARATIVE
3-31
K
WITH
65
0.1
300
NONE















EXAMPLE
3-32
K
WITH
65
0.1
300
90%Al + 10%Si
40


EXAMPLE
3-33
K
WITH
65
0.1
300
90%Al + 10%Si
40


OF
3-34
K
WITH
65
0.1
300
90%Al + 10%Si
40


PRESENT
3-35
K
WITH
65
0.1
300
90%Al + 10%Si
40


INVENTION
3-36
K
WITH
65
0.1
300
90%Al + 10%Si
40














COMPARATIVE
3-37
L
WITH
60
0.2
500
NONE















EXAMPLE
3-38
L
WITH
60
0.2
500
92%Sn + 8%Zn
26


EXAMPLE
3-39
L
WITH
60
0.2
500
92%Sn + 8%Zn
26


OF
3-40
L
WITH
60
0.2
500
92%Sn + 8%Zn
26


PRESENT
3-41
L
WITH
60
0.2
500
92%Sn + 8%Zn
26


INVENTION
3-42
L
WITH
60
0.2
500
92%Sn + 8%Zn
26













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
{200} PLANE
{222} PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
3-1
1
898
16
14
980
3600


EXAMPLE
3-2
1
898
22
10
980
3600


EXAMPLE
3-3
1
898
27
9
980
3600


OF
3-4
1
898
39
7.5
980
3600


PRESENT
3-5
1
898
42
6.4
980
3600


INVENTION
3-6
1
898
44
5.9
980
3600



3-7
0.01
898
34
7.7
1000
7200



3-8
0.01
898
39
7.6
1000
7200



3-9
0.01
898
41
6.3
1000
7200



3-10
0.01
898
42
5.9
1000
7200



3-11
0.01
898
42
5.6
1000
7200



3-12
0.01
898
41
5.7
1000
7200


COMPARATIVE
3-13
0.1
887
18
15
950
600


EXAMPLE
3-14
0.1
850
23
11
850
600


EXAMPLE
3-15
0.1
887
39
7.8
950
600


OF
3-16
0.1
887
39
7.8
1050
600


PRESENT
3-17
0.1
887
39
7.8
1150
600


INVENTION
3-18
0.1
887
39
7.8
1250
600


COMPARATIVE
3-19
0.2
905
17
13
1000
60


EXAMPLE
3-20
0.2
880
24
10
880
60


EXAMPLE
3-21
0.2
905
44
6.2
1000
60


OF
3-22
0.2
905
44
6.2
1100
60


PRESENT
3-23
0.2
905
44
6.2
1250
60


INVENTION
3-24
0.2
905
44
6.2
1350
60


COMPARATIVE
3-25
2
868
18
12
900
10


EXAMPLE
3-26
2
850
22
12
850
10


EXAMPLE
3-27
2
868
36
8.2
900
10


OF
3-28
2
868
36
8.2
1000
10


PRESENT
3-29
2
868
36
8.2
1100
10


INVENTION
3-30
2
868
36
8.2
1200
10


COMPARATIVE
3-31
0.1
921
14
12
1000
100


EXAMPLE
3-32
0.1
900
23
13
900
100


EXAMPLE
3-33
0.1
921
38
7.3
1000
100


OF
3-34
0.1
921
38
7.3
1100
100


PRESENT
3-35
0.1
921
38
7.3
1200
100


INVENTION
3-36
0.1
921
38
7.3
1300
100


COMPARATIVE
3-37
1
925
15
11
1000
0


EXAMPLE
3-38
1
900
24
12
900
0


EXAMPLE
3-39
1
925
41
7.1
1000
0


OF
3-40
1
925
41
7.1
1100
0


PRESENT
3-41
1
925
41
7.1
1200
0


INVENTION
3-42
1
925
41
7.1
1300
0













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
{200} PLANE
{222} PLANE
RATE
TANCE
{200} PLANE
{222} PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
3-1
13
13
50
183
13
13


EXAMPLE
3-2
23
10
50
183
23
10


EXAMPLE
3-3
36
6.8
50
183
36
6.8


OF
3-4
52
2.7
50
183
52
2.7


PRESENT
3-5
68
1.9
50
183
68
1.9


INVENTION
3-6
70
1.5
50
183
70
1.5



3-7
42
6.7
1
5
42
6.7



3-8
50
3.1
1
53
50
3.1



3-9
53
2.6
1
265
53
2.6



3-10
55
2.1
1
350
52
3.4



3-11
56
1.9
1
420
45
6.1



3-12
54
2.3
1
450
35
7.6


COMPARATIVE
3-13
13
13
0.1
100
13
13


EXAMPLE
3-14
26
10
0.1
100
26
10


EXAMPLE
3-15
47
5.3
0.1
100
47
5.3


OF
3-16
51
3.3
0.1
100
51
3.3


PRESENT
3-17
64
2.3
0.1
100
64
2.3


INVENTION
3-18
73
1.1
0.1
100
73
1.1


COMPARATIVE
3-19
13
13
5
75
13
13


EXAMPLE
3-20
27
9
5
76
27
9


EXAMPLE
3-21
54
2.6
5
76
54
2.6


OF
3-22
68
2.1
5
76
68
2.1


PRESENT
3-23
78
0.8
5
76
78
0.8


INVENTION
3-24
67
2.3
5
76
67
2.3


COMPARATIVE
3-25
13
13
0.5
300
13
13


EXAMPLE
3-26
24
10
0.5
300
24
10


EXAMPLE
3-27
41
6.8
0.5
300
41
6.8


OF
3-28
49
5.4
0.5
300
49
5.4


PRESENT
3-29
54
3.1
0.5
300
54
3.1


INVENTION
3-30
58
2.7
0.5
300
58
2.7


COMPARATIVE
3-31
13
13
10
150
13
13


EXAMPLE
3-32
25
10
10
160
25
10


EXAMPLE
3-33
47
5.9
10
160
47
5.9


OF
3-34
59
2.8
10
160
59
2.8


PRESENT
3-35
71
1.5
10
160
71
1.5


INVENTION
3-36
63
2.5
10
160
63
2.5


COMPARATIVE
3-37
13
13
500
250
13
13


EXAMPLE
3-38
25
11
500
270
25
11


EXAMPLE
3-39
43
6.3
500
270
43
6.3


OF
3-40
52
3.2
500
270
52
3.2


PRESENT
3-41
52
2.8
500
270
62
2.8


INVENTION
3-42
58
3
500
270
58
3









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5% or more was regarded as an alloy layer. Further, in finding the ratio of the α single phase region, the alloy region was decided as described in the following. In the conditions No. 3-1 to No. 3-12 using Al as the metal layers, a region where the Al content was 0.9 mass % or more was regarded as the alloy region. In the conditions No. 3-14 to No. 3-18 using Sb as the metal layers, a region where the Sb content was 3.6 mass % or more was regarded as the alloy region. In the conditions No. 3-20 to No. 3-24 using W as the metal layers, a region where the W content was 6.6 mass % or more was regarded as the alloy region. In the conditions No. 3-26 to No. 3-30 using Zn as the metal layers, a region where the Zn content was 7.2 mass % or more was regarded as the alloy region. In the conditions No. 3-32 to No. 3-36 using an Al—Si alloy as the metal layers, a region where the Al content was 0.9 mass % or more and the Si content was 0.2 mass % or more was regarded as the alloy region. In the conditions No. 3-38 to No. 3-42 using a Sn—Zn alloy as the metal layers, a region where the Sn content was 2.9 mass % or more and the Zn content was 0.6 mass % or more was regarded as the alloy region. Results of these are listed in Table 10.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Results of these are listed in Table 10.















TABLE 10








RATIO OF
ACCUMULATION
ACCUMULATION







ALLOYING
α SINGLE
DEGREE OF
DEGREE OF






CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs




No.
(%)
(%)
(%)
(%)
(T)
(T)
B50/Bs























COMPARATIVE
3-1
13
13
13
13
1.70
2.16
0.79


EXAMPLE
3-2
23
10
23
10
1.62
2.05
0.79


EXAMPLE
3-3
36
6.8
36
6.8
1.82
2.05
0.89


OF
3-4
52
2.7
52
2.7
1.85
2.05
0.90


PRESENT
3-5
68
1.9
68
1.9
1.89
2.05
0.92


INVENTION
3-6
70
1.5
70
1.5
1.91
2.05
0.93



3-7
100
100
42
6.7
1.80
2.05
0.88



3-8
100
100
50
3.1
1.85
2.05
0.90



3-9
100
25
53
2.6
1.87
2.05
0.91



3-10
100
10.8
55
2.1
1.87
2.05
0.91



3-11
95
3.8
56
1.9
1.85
2.05
0.90



3-12
75
2.1
54
2.3
1.80
2.05
0.88


COMPARATIVE
3-13
—
0
13
13
1.65
2.16
0.76


EXAMPLE
3-14
76
0.2
26
10
1.62
2.04
0.79


EXAMPLE
3-15
100
1.7
47
5.3
1.81
2.04
0.89


OF
3-16
100
3.8
51
3.3
1.84
2.04
0.90


PRESENT
3-17
100
7.5
64
2.3
1.86
2.04
0.91


INVENTION
3-18
100
8.4
73
1.1
1.88
2.04
0.92


COMPARATIVE
3-19
—
0
13
13
1.67
2.16
0.77


EXAMPLE
3-20
57
0.4
27
9
1.58
2.02
0.78


EXAMPLE
3-21
86
2.6
54
2.6
1.81
2.02
0.90


OF
3-22
100
6.8
68
2.1
1.83
2.02
0.91


PRESENT
3-23
100
10.1
78
0.8
1.87
2.02
0.93


INVENTION
3-24
100
13.9
67
2.3
1.84
2.02
0.91


COMPARATIVE
3-25
—
0
13
13
1.67
2.16
0.77


EXAMPLE
3-26
24
0.6
24
10
1.46
1.90
0.77


EXAMPLE
3-27
64
2.7
41
6.8
1.65
1.90
0.87


OF
3-28
89
5.8
49
5.4
1.67
1.90
0.88


PRESENT
3-29
100
12.7
54
3.1
1.71
1.90
0.90


INVENTION
3-30
100
19.5
58
2.7
1.73
1.90
0.91


COMPARATIVE
3-31
—
0
13
13
1.67
2.16
0.77


EXAMPLE
3-32
37
0.9
25
10
1.52
1.95
0.78


EXAMPLE
3-33
84
3.9
47
5.9
1.72
1.95
0.88


OF
3-34
100
8.5
59
2.8
1.78
1.95
0.91


PRESENT
3-35
100
14.6
71
1.5
1.82
1.95
0.93


INVENTION
3-36
100
21.7
63
2.5
1.80
1.95
0.92


COMPARATIVE
3-37
—
0
13
13
1.66
2.16
0.77


EXAMPLE
3-38
21
0.7
25
11
1.51
1.94
0.78


EXAMPLE
3-39
63
2.7
43
6.3
1.71
1.94
0.88


OF
3-40
88
5.6
52
3.2
1.75
1.94
0.90


PRESENT
3-41
100
10.6
62
2.8
1.77
1.94
0.61


INVENTION
3-42
100
17.8
58
3
1.76
1.94
0.91









As listed in Table 9, in examples of the present invention (conditions No. 3-3 to No. 3-12, No. 3-15 to No. 3-18, No. 3-21 to No. 3-24, No. 3-27 to No. 3-30, No. 3-33 to No. 3-36, and No. 3-39 to No. 3-42), the accumulation degree of the {200} planes in the α phase was high at each of the stages of the heat treatment. Further, as listed in Table 10, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were high. As listed in Table 10, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was not less than 30% nor more than 99% and the accumulation degree of the {222} planes in the α phase was not less than 0.01% nor more than 30% were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more. That is, according to the examples of the present invention, an excellent magnetic property was obtained.
On the other hand, in the conditions No. 3-1 and No. 3-2 being comparative examples, even though the metal layers were formed, a shear strain and a rolling reduction ratio were small, and they did not satisfy the requirement that “after the heating to the A3 point, the accumulation degree of the {200} planes in the α phase is 25% or more and the accumulation degree of the {222} planes in the α phase is 40% or less”, and therefore a high accumulation degree of the {200} planes in the α phase was not obtained and a good magnetic property was not obtained. In the conditions No. 3-13, No. 3-19, No. 3-25, No. 3-31, and No. 3-37 being comparative examples, since the metal layer was not formed, a high accumulation degree of the {200} planes in the α phase was not obtained and a good magnetic property was not obtained even though a large shear strain existed. In the conditions No. 3-14, No. 3-20, No. 3-26, No. 3-32, and No. 3-38 being comparative examples, since the heating temperature was lower than the A3 point, improvement in the accumulation degree of the {200} planes in the α phase owing to the γ-α transformation was not caused, and a good magnetic property was not obtained.
Fourth Experiment
In a fourth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 4-1 to condition No. 4-42) were studied.
Base metal plates (silicon steel plates) used in the fourth experiment contained components of the composition N listed in Table 11 and inevitable impurities, with the balance being Fe. The base metal plates were fabricated in such a manner that an ingot was produced by vacuum melting, followed by hot rolling and cold rolling. In the hot rolling, the ingot with a 230 mm thickness heated to 1200° C. was thinned to a 10.0 mm thickness, a 5.0 mm thickness, a 4.0 mm thickness, and a 2.0 mm thickness, whereby four kinds of hot-rolled plates were obtained. An actually measured value of the A3 point at which the base metal plates (silicon steel plates) used in the fourth experiment transformed to a γ single layer was 1010° C.









TABLE 11








COMPONENT ELEMENT (mass %)
A3 POINT

















COMPOSITION
C
Si
Mn
Al
P
N
S
O
OTHERS
(° C.)




















N
0.0002
1.4
0.005
0.1
0.0004
0.005
<0.0004
0.003

1010


O
0.0002
1.1
0.1
0.3
0.0004
0.005
<0.0004
0.003

1005


P
0.0002
1.3
0.2
0.2
0.0004
0.005
<0.0004
0.003

1010


Q
0.0002
0.9
0.15
0.6
0.0004
0.004
<0.0004
0.003

1020


R
0.0003
1.0
0.15
0.4
0.0003
0.004
<0.0004
0.003

1010


S
0.0002
1.5
0.08
0.5
0.0003
0.004
<0.0004
0.003

1080


T
0.0003
0.005
0.12
0.6
0.0004
0.004
<0.0004
0.003

1020


U
0.0003
0.6
0.1
0.65
0.0004
0.004
<0.0004
0.003
Cr: 2%
1000


V
0.0003
0.8
0.1
0.5
0.0004
0.004
<0.0004
0.003
Mo: 1%
1000


W
0.0003
0.2
0.05
0.7
0.0004
0.004
<0.0004
0.003
V: 0.5%
1010









The cold rolling was performed under the following conditions. In the conditions No. 4-1 to 4-7, the hot-rolled plates with a 2.0 mm thickness were pickled to remove scales, and thereafter were rolled to a 0.1 mm thickness. A rolling reduction ratio at this time was 95%. In the conditions No. 4-8 to 4-14, the hot-rolled plates with a 4.0 mm thickness were pickled to remove scales, and thereafter were rolled to a 0.1 mm thickness. A rolling reduction ratio at this time was 97.5%. In the conditions No. 4-15 to 4-21, the hot-rolled steel plates with a 2.0 mm thickness were subjected to shot blasting as hard surface machining on both surfaces, and thereafter were rolled to a 0.1 mm thickness. A rolling reduction ratio at this time was 95%. In the shot blasting, iron beads with a 1 mm to 3 mm diameter were made to continuously collide with the both surfaces of the base metal plates for 10 seconds each. In the conditions No. 4-22 to 4-28, the hot-rolled plates with a 5.0 mm thickness were pickled to remove scales and thereafter were rolled to a 0.25 mm thickness. A rolling reduction ratio at this time was 95%. In the conditions No. 4-29 to 4-35, the hot-rolled plates with a 10.0 mm thickness were pickled to remove scales, and thereafter were rolled to a 0.25 mm thickness. A rolling reduction ratio at this time was 97.5%. In the conditions No. 4-36 to 4-42, the hot-rolled plates with a 5.0 mm thickness were subjected to shot blasting as hard surface machining on both surfaces and thereafter were cold-rolled to a 0.25 mm thickness. A rolling reduction ratio at this time was 95%. In this shot blasting, iron beads with a 1 mm to 3 mm diameter were made to continuously collide with the both surfaces of the base metal plates for ten seconds each.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 12.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Al layers as the metal layers were formed on the front surface and the rear surface of each of the base metal plates by a vapor deposition method, except in the conditions No. 4-1, No. 4-8, No. 4-15, No. 4-22, No. 4-29, and No. 4-36. Thickness of each of the Al layers (total thickness on the both surfaces) is listed in Table 12.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200}planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 12.









TABLE 12








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSTTY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
4-1
N
WITHOUT
95
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
4-2
N
WITHOUT
95
1 × 1015
100
Al
9


OF
4-3
N
WITHOUT
95
1 × 1015
100
Al
9


PRESENT
4-4
N
WITHOUT
95
1 × 1015
100
Al
9


INVENTION
4-5
N
WITHOUT
95
1 × 1015
100
Al
9



4-6
N
WITHOUT
95
1 × 1015
100
Al
9



4-7
N
WITHOUT
95
1 × 1015
100
Al
9














COMPARATIVE
4-8
N
WITHOUT
97.5
1 × 1016
100
NONE


EXAMPLE






















EXAMPLE
4-9
N
WITHOUT
97.5
1 × 1016
100
Al
9


OF
4-10
N
WITHOUT
97.5
1 × 1016
100
Al
9


PRESENT
4-11
N
WITHOUT
97.5
1 × 1016
100
Al
9


INVENTION
4-12
N
WITHOUT
97.5
1 × 1016
100
Al
9



4-13
N
WITHOUT
97.5
1 × 1016
100
Al
9



4-14
N
WITHOUT
97.5
1 × 1016
100
Al
9














COMPARATIVE
4-15
N
WITH
95
8 × 1016
100
NONE


EXAMPLE






















EXAMPLE
4-18
N
WITH
95
8 × 1016
100
Al
9


OF
4-17
N
WITH
95
8 × 1016
100
Al
9


PRESENT
4-18
N
WITH
95
8 × 1016
100
Al
9


INVENTION
4-19
N
WITH
95
8 × 1016
100
Al
9



4-20
N
WITH
95
8 × 1016
100
Al
9



4-21
N
WITH
95
8 × 1016
100
Al
9














COMPARATIVE
4-22
N
WITHOUT
95
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
4-23
N
WITHOUT
95
1 × 1015
250
Al
22


OF
4-24
N
WITHOUT
95
1 × 1015
250
Al
22


PRESENT
4-25
N
WITHOUT
95
1 × 1015
250
Al
22


INVENTION
4-26
N
WITHOUT
95
1 × 1015
250
Al
22



4-27
N
WITHOUT
95
1 × 1015
250
Al
22



4-28
N
WITHOUT
95
1 × 1015
250
Al
22














COMPARATIVE
4-29
N
WITHOUT
97.5
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
4-30
N
WITHOUT
97.5
1 × 1016
250
Al
22


OF
4-31
N
WITHOUT
97.5
1 × 1016
250
Al
22


PRESENT
4-32
N
WITHOUT
97.5
1 × 1016
250
Al
22


INVENTION
4-33
N
WITHOUT
97.5
1 × 1016
250
Al
22



4-34
N
WITHOUT
97.5
1 × 1016
250
Al
22



4-35
N
WITHOUT
97.5
1 × 1016
250
Al
22














COMPARATIVE
4-36
N
WITH
95
8 × 1016
250
NONE


EXAMPLE






















EXAMPLE
4-37
N
WITH
95
8 × 1016
250
Al
22


OF
4-38
N
WITH
95
8 × 1016
250
Al
22


PRESENT
4-39
N
WITH
95
8 × 1016
250
Al
22


INVENTION
4-40
N
WITH
95
8 × 1016
250
Al
22



4-41
N
WITH
95
8 × 1016
250
Al
22



4-42
N
WITH
95
8 × 1016
250
Al
22













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
{200} PLANE
{22} PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
4-1
10
1010
16
14
1050
2


EXAMPLE









EXAMPLE
4-2
10
1010
26
14
1010
2


OF
4-3
10
1010
26
14
1050
2


PRESENT
4-4
10
1010
26
14
1050
5


INVENTION
4-5
10
1010
26
14
1050
30



4-6
10
1010
26
14
1050
120



4-7
10
1010
26
14
1050
360


COMPARATIVE
4-8
10
1010
16
14
1050
2


EXAMPLE









EXAMPLE
4-9
10
1010
40
3.8
1010
2


OF
4-10
10
1010
40
3.8
1050
2


PRESENT
4-11
10
1010
40
3.8
1050
5


INVENTION
4-12
10
1010
40
3.8
1050
30



4-13
10
1010
40
3.8
1050
120



4-14
10
1010
40
3.8
1050
360


COMPARATIVE
4-15
10
1010
15
13
1050
2


EXAMPLE









EXAMPLE
4-18
10
1010
59
2.9
1050
2


OF
4-17
10
1010
59
2.9
1050
2


PRESENT
4-18
10
1010
59
2.9
1050
5


INVENTION
4-19
10
1010
59
2.9
1050
30



4-20
10
1010
59
2.9
1050
120



4-21
10
1010
59
2.9
1050
360


COMPARATIVE
4-22
10
1010
16
14
1010
2


EXAMPLE









EXAMPLE
4-23
10
1010
26
14
1010
2


OF
4-24
10
1010
27
13
1100
3


PRESENT
4-25
10
1010
27
13
1100
7


INVENTION
4-26
10
1010
27
13
1100
35



4-27
10
1010
27
13
1100
140



4-28
10
1010
27
13
1100
420


COMPARATIVE
4-29
10
1010
16
14
1010
2


EXAMPLE









EXAMPLE
4-30
10
1010
40
3.8
1010
2


OF
4-31
10
1010
42
3.2
1100
3


PRESENT
4-32
10
1010
42
3.2
1100
7


INVENTION
4-33
10
1010
42
3.2
1100
35



4-34
10
1010
42
3.2
1100
140



4-35
10
1010
42
3.2
1100
420


COMPARATIVE
4-36
10
1010
15
13
1010
2


EXAMPLE









EXAMPLE
4-37
10
1010
59
2.9
1050
2


OF
4-38
10
1010
58
2.8
1100
3


PRESENT
4-39
10
1010
58
2.8
1100
7


INVENTION
4-40
10
1010
58
2.8
1100
35



4-41
10
1010
58
2.8
1100
140



4-42
10
1010
58
2.8
1100
420













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
{200} PLANE
{222} PLANE
RATE
TANCE
{200} PLANE
{222} PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
4-1
13
13
100
50
13
13


EXAMPLE









EXAMPLE
4-2
30
11
100
54
30
11


OF
4-3
31
10
100
54
31
10


PRESENT
4-4
31
10
100
54
31
10


INVENTION
4-5
31
10
100
54
31
10



4-6
31
10
100
54
31
10



4-7
31
10
100
54
31
10


COMPARATIVE
4-8
13
13
100
50
13
13


EXAMPLE









EXAMPLE
4-9
45
5.2
100
54
45
5.2


OF
4-10
53
2.7
100
54
53
2.8


PRESENT
4-11
53
2.7
100
54
53
2.8


INVENTION
4-12
53
2.7
100
54
53
2.8



4-13
53
2.7
100
54
53
2.8



4-14
53
2.7
100
54
53
2.8


COMPARATIVE
4-15
13
13
100
50
13
13


EXAMPLE









EXAMPLE
4-18
62
2.1
100
54
62
2.1


OF
4-17
75
1.3
100
54
75
1.3


PRESENT
4-18
75
1.3
100
54
75
1.3


INVENTION
4-19
75
1.3
100
54
75
1.3



4-20
75
1.3
100
54
75
1.3



4-21
75
1.3
100
54
75
1.3


COMPARATIVE
4-22
13
13
100
125
13
13


EXAMPLE









EXAMPLE
4-23
30
11
100
136
30
11


OF
4-24
32
9
100
136
32
9


PRESENT
4-25
32
9
100
136
32
9


INVENTION
4-26
32
9
100
136
32
9



4-27
32
9
100
135
32
9



4-28
32
9
100
136
32
9


COMPARATIVE
4-29
13
13
100
125
13
13


EXAMPLE









EXAMPLE
4-30
44
4.8
100
136
44
4.8


OF
4-31
56
2.1
100
136
56
2.1


PRESENT
4-32
56
2.1
100
136
56
2.1


INVENTION
4-33
56
2.1
100
136
56
2.1



4-34
56
2.1
100
136
56
2.1



4-35
56
2.1
100
136
56
2.1


COMPARATIVE
4-36
13
13
100
125
13
13


EXAMPLE









EXAMPLE
4-37
61
2.3
100
136
61
2.3


OF
4-38
82
0.8
100
136
82
0.8


PRESENT
4-39
82
0.8
100
136
82
0.8


INVENTION
4-40
82
0.8
108
136
82
0.8



4-41
82
0.8
100
136
82
0.8



4-42
82
0.8
100
138
82
0.8









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each Fe-based metal plate were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Al content was 0.9 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 13.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/100) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 13.
















TABLE 13








RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF







CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs

W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
B50/Bs
(W/kg)
























COMPARATIVE
4-1
0
0
13
13
1.60
2.05
0.78
92


EXAMPLE











EXAMPLE
4-2
9
0.1
30
11
1.74
2.05
0.85
65


OF
4-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
4-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
4-5
100
35
30
10
1.74
2.05
0.85
37



4-6
100
73
30
10
1.74
2.05
0.85
43



4-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
4-8
0
0
13
13
1.60
2.05
0.78
90


EXAMPLE











EXAMPLE
4-9
10
0.3
45
5.2
1.78
2.05
0.87
63


OF
4-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
4-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
4-12
100
42
53
2.7
1.85
2.05
0.90
33



4-13
100
71
53
2.7
1.85
2.05
0.90
38



4-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
4-15
0
0
13
13
1.62
2.05
0.79
92


EXAMPLE











EXAMPLE
4-16
8
0.2
62
2.1
1.89
2.05
0.92
62


OF
4-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
4-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
4-19
100
37
75
1.3
1.95
2.05
0.95
28



4-20
100
72
76
1.4
1.97
2.05
0.96
33



4-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
4-22
0
0
13
13
1.60
2.05
0.78
98


EXAMPLE











EXAMPLE
4-23
7
0.5
30
11
1.74
2.05
0.85
63


OF
4-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
4-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
4-26
100
45
32
9
1.74
2.05
0.85
37



4-27
100
72
32
9
1.74
2.05
0.85
42



4-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
4-29
0
0
13
13
1.60
2.05
0.78
96


EXAMPLE











EXAMPLE
4-30
6
0.3
44
4.8
1.80
2.05
0.88
65


OF
4-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
4-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
4-33
100
38
56
2.2
1.87
2.05
0.91
32



4-34
100
71
56
2.1
1.85
2.05
0.90
38



4-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
4-36
0
0
13
13
1.62
2.05
0.79
101


EXAMPLE











EXAMPLE
4-37
8
0.2
61
2.3
1.91
2.05
0.93
61


OF
4-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
4-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
4-40
100
41
82
0.8
1.97
2.05
0.96
26



4-41
100
76
82
0.8
1.95
2.05
0.95
32



4-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 12, in examples of the present invention (conditions No. 4-2 to No. 4-7, No. 4-9 to No. 4-14, No. 4-16 to No. 4-21, No. 4-23 to No. 4-28, No. 4-30 to No. 4-35, No. 4-37 to No. 4-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 13, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 13, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1k maintained a higher property level. Further, it could be confirmed that the core loss W10/1k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Fifth Experiment
In a fifth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 5-1 to condition No. 5-42) were studied.
Base metal plates (silicon steel plates) used in the fifth experiment contained components of the composition O listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the fifth experiment transformed to a γ single phase was 1005° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 5-1 to the condition No. 5-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 14.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Si layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a vapor deposition method, except in the conditions No. 5-1, No. 5-8, No. 5-15, No. 5-22, No. 5-29, and No. 5-36. Thickness of each of the Si layers (total thickness on the both surfaces) is listed in Table 14.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 14.









TABLE 14








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSITY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
5-1
O
WITHOUT
95
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
5-2
O
WITHOUT
95
1 × 1015
100
Si
10


OF
5-3
O
WITHOUT
95
1 × 1015
100
Si
10


PRESENT
5-4
O
WITHOUT
95
1 × 1015
100
Si
10


INVENTION
5-5
O
WITHOUT
95
1 × 1015
100
Si
10



5-6
O
WITHOUT
95
1 × 1015
100
Si
10



5-7
O
WITHOUT
95
1 × 1015
100
Si
10














COMPARATIVE
5-8
O
WITHOUT
97.5
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
5-9
O
WITHOUT
97.5
1 × 1015
100
Si
10


OF
5-10
O
WITHOUT
97.5
1 × 1015
100
Si
10


PRESENT
5-11
O
WITHOUT
97.5
1 × 1015
100
Si
10


INVENTION
5-12
O
WITHOUT
97.5
1 × 1015
100
Si
10



5-13
O
WITHOUT
97.5
1 × 1015
100
Si
10



5-14
O
WITHOUT
97.5
1 × 1015
100
Si
10














COMPARATIVE
5-15
O
WITH
95
8 × 1015
100
NONE


EXAMPLE






















EXAMPLE
5-16
O
WITH
95
8 × 1015
100
Si
10


OF
5-17
O
WITH
95
8 × 1015
100
Si
10


PRESENT
5-18
O
WITH
95
8 × 1015
100
Si
10


INVENTION
5-19
O
WITH
95
8 × 1015
100
Si
10



5-20
O
WITH
95
8 × 1015
100
Si
10



5-21
O
WITH
95
8 × 1015
100
Si
10














COMPARATIVE
5-22
O
WITHOUT
95
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
5-23
O
WITHOUT
95
1 × 1015
250
Si
25


OF
5-24
O
WITHOUT
95
1 × 1015
250
Si
25


PRESENT
5-25
O
WITHOUT
95
1 × 1015
250
Si
25


INVENTION
5-26
O
WITHOUT
95
1 × 1015
250
Si
25



5-27
O
WITHOUT
95
1 × 1015
250
Si
25



5-28
O
WITHOUT
95
1 × 1015
250
Si
25














COMPARATIVE
5-29
O
WITHOUT
97.5
1 × 1016
250
NONE


EXAMPLE






















EXAMPLE
5-30
O
WITHOUT
97.5
1 × 1016
250
Si
25


OF
5-31
O
WITHOUT
97.5
1 × 1016
250
Si
25


PRESENT
5-32
O
WITHOUT
97.5
1 × 1016
250
Si
25


INVENTION
5-33
O
WITHOUT
97.5
1 × 1016
250
Si
25



5-34
O
WITHOUT
97.5
1 × 1016
250
Si
25



5-35
O
WITHOUT
97.5
1 × 1016
250
Si
25














COMPARATIVE
5-36
O
WITH
95
8 × 1016
250
NONE


EXAMPLE






















EXAMPLE
5-37
O
WITH
95
8 × 1016
250
Si
25


OF
5-38
O
WITH
95
8 × 1016
250
Si
25


PRESENT
5-39
O
WITH
85
8 × 1016
250
Si
25


INVENTION
5-40
O
WITH
95
8 × 1016
250
Si
25



5-41
O
WITH
95
8 × 1016
250
Si
25



5-42
O
WITH
95
8 × 1016
250
Si
25













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
{200} PLANE
{222} PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
5-1
20
1005
15
14
1050
2


EXAMPLE









EXAMPLE
5-2
20
1005
25
15
1005
2


OF
5-3
20
1005
25
15
1050
2


PRESENT
5-4
20
1005
25
15
1050
5


INVENTION
5-5
20
1005
25
15
1050
30



5-6
20
1005
25
15
1050
120



5-7
20
1005
25
15
1050
360


COMPARATIVE
5-8
20
1005
17
13
1050
2


EXAMPLE









EXAMPLE
5-9
20
1005
38
4.1
1005
2


OF
5-10
20
1005
38
4.1
1050
2


PRESENT
5-11
20
1005
38
4.1
1050
5


INVENTION
5-12
20
1005
38
4.1
1050
30



5-13
20
1005
38
4.1
1050
120



5-14
20
1005
38
4.1
1050
360


COMPARATIVE
5-15
20
1005
15
13
1050
2


EXAMPLE









EXAMPLE
5-16
20
1005
56
2.8
1005
2


OF
5-17
20
1005
56
2.8
1050
2


PRESENT
5-18
20
1005
56
2.8
1050
5


INVENTION
5-19
20
1005
56
2.8
1050
30



5-20
20
1005
56
2.8
1050
120



5-21
20
1005
56
2.8
1050
360


COMPARATIVE
5-22
20
1005
16
14
1100
2


EXAMPLE









EXAMPLE
5-23
20
1005
26
14
1005
2


OF
5-24
20
1005
26
14
1100
3


PRESENT
5-25
20
1005
26
14
1100
7


INVENTION
5-26
20
1005
26
14
1100
35



5-27
20
1005
26
14
1100
140



5-28
20
1005
26
14
1100
420


COMPARATIVE
5-29
20
1005
17
13
1100
2


EXAMPLE









EXAMPLE
5-30
20
1005
39
3.8
1005
2


OF
5-31
20
1005
39
3.8
1100
3


PRESENT
5-32
20
1005
39
3.8
1100
7


INVENTION
5-33
20
1005
39
3.8
1100
35



5-34
20
1005
39
3.8
1100
140



5-35
20
1005
39
3.8
1100
420


COMPARATIVE
5-36
10
1005
17
14
1100
2


EXAMPLE









EXAMPLE
5-37
20
1005
54
2.7
1005
2


OF
5-38
20
1005
54
2.7
1100
3


PRESENT
5-39
20
1005
54
2.7
1100
7


INVENTION
5-40
20
1005
54
2.7
1100
35



5-41
20
1005
54
2.7
1100
140



5-42
20
1005
54
2.7
1100
420













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
{200} PLANE
{222} PLANE
RATE
TANCE
{200} PLANE
{222} PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
5-1
13
13
100
50
13
13


EXAMPLE









EXAMPLE
5-2
31
12
100
54
31
12


OF
5-3
32
9
20
54
32
9


PRESENT
5-4
32
9
20
54
32
9


INVENTION
5-5
32
9
20
54
32
9



5-6
32
9
20
54
32
9



5-7
32
9
20
54
32
9


COMPARATIVE
5-8
13
13
100
50
13
13


EXAMPLE









EXAMPLE
5-9
43
5.7
100
54
43
5.7


OF
5-10
55
2.1
20
54
55
2.1


PRESENT
5-11
55
2.1
20
54
55
2.1


INVENTION
5-12
55
2.1
20
54
55
2.1



5-13
55
2.1
20
54
55
2.1



5-14
55
2.1
20
54
55
2.1


COMPARATIVE
5-15
13
13
100
50
13
13


EXAMPLE









EXAMPLE
5-16
58
2.4
100
54
58
2.4


OF
5-17
78
1.1
20
54
78
1.1


PRESENT
5-18
78
1.1
20
54
78
1.1


INVENTION
5-19
78
1.1
20
54
78
1.1



5-20
78
1.1
20
54
78
1.1



5-21
78
1.1
20
54
78
1.1


COMPARATIVE
5-22
13
13
100
125
13
13


EXAMPLE









EXAMPLE
5-23
30
12
100
136
30
12


OF
5-24
31
10
20
136
31
10


PRESENT
5-25
31
10
20
136
31
10


INVENTION
5-26
31
10
20
136
31
10



5-27
31
10
20
136
31
10



5-28
31
10
20
136
31
10


COMPARATIVE
5-29
13
13
100
125
13
13


EXAMPLE









EXAMPLE
5-30
42
5
100
136
42
5


OF
5-31
58
1.9
20
136
58
1.9


PRESENT
5-32
58
1.9
20
136
58
1.9


INVENTION
5-33
58
1.9
20
136
58
1.9



5-34
58
1.9
20
136
58
1.9



5-35
58
1.9
20
136
58
1.9


COMPARATIVE
5-36
13
13
100
125
13
13


EXAMPLE









EXAMPLE
5-37
52
2.1
100
136
62
2.1


OF
5-38
87
0.3
20
136
87
0.3


PRESENT
5-39
87
0.3
20
136
87
0.3


INVENTION
5-40
87
0.3
20
136
87
0.3



5-41
87
0.3
20
136
87
0.3



5-42
87
0.3
20
136
87
0.3









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each Fe-based metal plate were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Si content was 1.9 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 15.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 15.
















TABLE 15








RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF







CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs

W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
B50/Bs
(W/kg)
























COMPARATIVE
5-1
0
0
13
13
1.61
2.07
0.78
93


EXAMPLE











EXAMPLE
5-2
8
0.2
31
12
1.76
2.07
0.85
64


OF
5-3
67
2.1
32
9
1.78
2.07
0.86
59


PRESENT
5-4
89
7.6
32
9
1.78
2.07
0.86
45


INVENTION
5-5
100
40
32
9
1.78
2.07
0.86
38



5-6
100
71
32
9
1.78
2.07
0.86
42



5-7
100
95
32
9
1.78
2.07
0.86
59


COMPARATIVE
5-8
0
0
13
13
1.61
2.07
0.78
91


EXAMPLE











EXAMPLE
5-9
10
0.3
43
5.7
1.80
2.07
0.87
62


OF
5-10
51
1.2
55
2.1
1.88
2.07
0.91
53


PRESENT
5-11
82
5.9
55
2.1
1.88
2.07
0.91
41


INVENTION
5-12
100
38
55
2.1
1.88
2.07
0.91
32



5-13
100
72
55
2.1
1.88
2.07
0.91
35



5-14
100
89
55
2.1
1.88
2.07
0.91
53


COMPARATIVE
5-15
0
0
13
13
1.64
2.07
0.79
94


EXAMPLE











EXAMPLE
5-18
8
0.2
58
2.4
1.90
2.07
0.92
61


OF
5-17
72
2.3
78
1.1
1.99
2.07
0.96
47


PRESENT
5-18
87
6.8
78
1.1
1.99
2.07
0.96
40


INVENTION
5-19
100
42
78
1.1
1.99
2.07
0.96
29



5-20
100
62
78
1.1
1.99
2.07
0.96
32



5-21
100
90
78
1.1
1.99
2.07
0.96
48


COMPARATIVE
5-22
0
0
13
13
1.61
2.07
0.78
102


EXAMPLE











EXAMPLE
5-23
7
0.5
30
12
1.76
2.07
0.85
61


OF
5-24
62
1.6
31
10
1.78
2.07
0.86
59


PRESENT
5-25
86
7.1
31
10
1.78
2.07
0.86
43


INVENTION
5-26
100
32
31
10
1.78
2.07
0.86
36



5-27
100
63
31
10
1.78
2.07
0.86
41



5-28
100
100
31
10
1.78
2.07
0.86
57


COMPARATIVE
5-29
0
0
13
13
1.61
2.07
0.78
97


EXAMPLE











EXAMPLE
5-30
6
0.3
42
5
1.82
2.07
0.88
62


OF
5-31
46
1.1
58
1.9
1.86
2.07
0.90
53


PRESENT
5-32
82
8.3
58
1.9
1.86
2.07
0.90
41


INVENTION
5-33
100
43
58
1.9
1.86
2.07
0.90
33



5-34
100
72
58
1.9
1.86
2.07
0.90
37



5-35
100
98
58
1.9
1.86
2.07
0.90
54


COMPARATIVE
5-36
0
0
13
13
1.64
2.07
0.79
98


EXAMPLE











EXAMPLE
5-37
8
0.2
62
2.1
1.93
2.07
0.93
64


OF
5-38
69
3.2
87
0.3
1.99
2.07
0.96
46


PRESENT
5-39
89
8.1
87
0.3
1.99
2.07
0.96
40


INVENTION
5-40
100
45
87
0.3
1.99
2.07
0.96
27



5-41
100
68
87
0.3
1.99
2.07
0.96
34



5-42
100
92
87
0.3
1.99
2.07
0.96
46









As listed in Table 14, in examples of the present invention (conditions No. 5-2 to No. 5-7, No. 5-9 to No. 5-14, No. 5-16 to No. 5-21, No. 5-23 to No. 5-28, No. 5-30 to No. 5-35, No. 5-37 to No. 5-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 15, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 15, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1k maintained a higher property level. Further, it could be confirmed that the core loss W10/1k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Sixth Experiment
In a sixth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 6-1 to condition No. 6-42) were studied.
Base metal plates (silicon steel plates) used in the sixth experiment contained components of the composition P listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the sixth experiment transformed to a γ single phase was 1010° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 6-1 to the condition No. 6-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 16.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Sn layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by an electroplating method, except in the conditions No. 6-1, No. 6-8, No. 6-15, No. 6-22, No. 6-29, and No. 6-36. Thickness of each of the Sn layers (total thickness on the both surfaces) is listed in Table 16.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 16.









TABLE 16








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSITY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
6-1
P
WITHOUT
95
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
6-2
P
WITHOUT
95
1 × 1015
100
Sn
3.2


OF
6-3
P
WITHOUT
95
1 × 1015
100
Sn
3.2


PRESENT
6-4
P
WITHOUT
95
1 × 1015
100
Sn
3.2


INVENTION
6-5
P
WITHOUT
95
1 × 1015
100
Sn
3.2



6-6
P
WITHOUT
95
1 × 1015
100
Sn
3.2



6-7
P
WITHOUT
95
1 × 1015
100
Sn
3.2














COMPARATIVE
6-8
P
WITHOUT
97.5
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
6-9
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2


OF
6-10
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2


PRESENT
6-11
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2


INVENTION
6-12
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2



6-13
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2



6-14
P
WITHOUT
97.5
1 × 1016
100
Sn
3.2














COMPARATIVE
6-15
P
WITH
95
8 × 1016
100
NONE


EXAMPLE






















EXAMPLE
6-16
P
WITH
95
8 × 1016
100
Sn
3.2


OF
6-17
P
WITH
95
8 × 1016
100
Sn
3.2


PRESENT
6-18
P
WITH
95
8 × 1016
100
Sn
3.2


INVENTION
6-19
P
WITH
95
8 × 1016
100
Sn
3.2



6-20
P
WITH
95
8 × 1016
100
Sn
3.2



6-21
P
WITH
95
8 × 1016
100
Sn
3.2














COMPARATIVE
6-22
P
WITHOUT
95
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
6-23
P
WITHOUT
95
1 × 1015
250
Sn
8


OF
6-24
P
WITHOUT
65
1 × 1015
250
Sn
8


PRESENT
6-25
P
WITHOUT
95
1 × 1015
250
Sn
8


INVENTION
6-26
P
WITHOUT
95
1 × 1015
250
Sn
8



6-27
P
WITHOUT
95
1 × 1015
250
Sn
8



6-28
P
WITHOUT
95
1 × 1015
250
Sn
8














COMPARATIVE
6-29
P
WITHOUT
97.5
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
6-30
P
WITHOUT
97.5
1 × 1015
250
Sn
8


OF
6-31
P
WITHOUT
97.5
1 × 1015
250
Sn
8


PRESENT
6-32
P
WITHOUT
97.5
1 × 1015
250
Sn
8


INVENTION
6-33
P
WITHOUT
97.5
1 × 1015
250
Sn
8



6-34
P
WITHOUT
97.5
1 × 1015
250
Sn
8



6-35
P
WITHOUT
97.5
1 × 1015
250
Sn
8














COMPARATIVE
6-36
P
WITH
95
8 × 1015
250
NONE


EXAMPLE






















EXAMPLE
6-37
P
WITH
95
8 × 1018
250
Sn
8


OF
6-38
P
WITH
95
8 × 1018
250
Sn
8


PRESENT
6-39
P
WITH
95
8 × 1018
250
Sn
8


INVENTION
6-40
P
WITH
95
8 × 1018
250
Sn
8



6-41
P
WITH
95
8 × 1018
250
Sn
8



6-42
P
WITH
95
8 × 1018
250
Sn
8













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
{200} PLANE
{222} PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
6-1
10
1010
18
13
1050
2


EXAMPLE









EXAMPLE
6-2
10
1010
26
14
1010
2


OF
6-3
10
1010
26
14
1050
2


PRESENT
6-4
10
1010
26
14
1050
5


INVENTION
6-5
10
1010
26
14
1050
30



6-6
10
1010
26
14
1050
120



6-7
10
1010
26
14
1050
360


COMPARATIVE
6-8
10
1010
18
13
1050
2


EXAMPLE









EXAMPLE
6-9
10
1010
35
5
1010
2


OF
6-10
10
1010
35
5
1050
2


PRESENT
6-11
10
1010
35
5
1050
5


INVENTION
6-12
10
1010
35
5
1050
30



6-13
10
1010
35
5
1050
120



6-14
10
1010
35
5
1050
360


COMPARATIVE
6-15
10
1010
18
13
1050
2


EXAMPLE









EXAMPLE
6-16
10
1010
60
2.5
1010
2


OF
6-17
10
1010
60
2.5
1050
2


PRESENT
6-18
10
1010
60
2.5
1050
5


INVENTION
6-19
10
1010
60
2.5
1050
30



6-20
10
1010
60
2.5
1050
120



6-21
10
1010
60
2.5
1050
360


COMPARATIVE
6-22
10
1010
18
13
1100
2


EXAMPLE









EXAMPLE
6-23
10
1010
25
16
1010
2


OF
6-24
10
1010
25
16
1100
3


PRESENT
6-25
10
1010
25
16
1100
7


INVENTION
6-26
10
1010
25
16
1100
35



6-27
10
1010
25
16
1100
140



6-28
10
1010
25
16
1100
420


COMPARATIVE
6-29
10
1010
18
13
1100
2


EXAMPLE









EXAMPLE
6-30
10
1010
37
4.1
1010
2


OF
6-31
10
1010
37
4.1
1100
3


PRESENT
6-32
10
1010
37
4.1
1100
7


INVENTION
6-33
10
1010
37
4.1
1100
35



6-34
10
1010
37
4.1
1100
140



6-35
10
1010
37
4.1
1100
420


COMPARATIVE
6-36
10
1010
18
13
1100
2


EXAMPLE









EXAMPLE
6-37
10
1010
57
2.5
1010
2


OF
6-38
10
1010
57
2.5
1100
3


PRESENT
6-39
10
1010
57
2.5
1100
7


INVENTION
6-40
10
1010
57
2.5
1100
35



6-41
10
1010
57
2.5
1100
140



6-42
10
1010
57
2.5
1100
420













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
[200] PLANE
[222] PLANE
RATE
TANCE
[200] PLANE
{222} PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
6-1
13
13
5
50
13
13


EXAMPLE









EXAMPLE
6-2
30
10
5
54
30
10


OF
6-3
33
8
5
54
33
8


PRESENT
6-4
33
8
5
54
33
8


INVENTION
6-5
33
8
5
54
33
8



6-6
33
8
5
54
33
8



6-7
33
8
5
54
33
8


COMPARATIVE
6-8
13
13
5
54
13
13


EXAMPLE









EXAMPLE
6-9
43
42
5
54
43
4.2


OF
6-10
54
1.8
5
54
54
1.8


PRESENT
6-11
54
1.8
5
54
54
1.8


INVENTION
6-12
54
1.8
5
54
54
1.8



6-13
54
1.8
5
54
54
1.8



6-14
54
1.8
5
54
54
1.8


COMPARATIVE
6-15
13
13
5
50
13
13


EXAMPLE









EXAMPLE
6-16
64
2.2
5
54
64
22


OF
6-17
80
0.9
5
54
80
0.9


PRESENT
6-18
80
0.9
5
54
80
0.9


INVENTION
6-19
80
0.9
5
54
80
0.9



6-20
80
0.9
5
54
80
0.9



6-21
60
0.9
5
54
80
0.9


COMPARATIVE
6-22
13
13
5
125
13
13


EXAMPLE









EXAMPLE
6-23
30
10
5
138
30
10


OF
6-24
31
9
5
136
31
9


PRESENT
6-25
31
9
5
138
31
9


INVENTION
6-26
31
9
5
136
31
9



6-27
31
9
5
136
31
9



6-28
31
9
5
136
31
9


COMPARATIVE
6-29
13
13
5
125
13
13


EXAMPLE









EXAMPLE
6-30
42
4.9
5
136
42
4.9


OF
6-31
55
2.3
5
136
55
2.3


PRESENT
6-32
55
2.3
5
136
55
2.3


INVENTION
6-33
55
2.3
5
136
55
2.3



6-34
55
2.3
5
136
55
2.3



6-35
55
2.3
5
136
55
2.3


COMPARATIVE
6-36
13
13
5
125
13
13


EXAMPLE









EXAMPLE
6-37
62
2.1
5
136
62
2.1


OF
6-38
74
0.3
5
136
74
0.3


PRESENT
6-39
74
0.3
5
136
74
0.3


INVENTION
6-40
74
0.3
5
136
74
0.3



6-41
74
0.3
5
136
74
0.3



6-42
74
0.3
5
136
74
0.3









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each Fe-based metal plate were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Sn content was 3.0 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 17.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 17.
















TABLE 17









ACCUMULATION










RATIO OF
DEGREE OF
ACCUMULATION








ALLOYING
α SINGLE
{2001
DEGREE OF







CONDITION
RATE
PHASE
PLANE
{222} PLANE
B50
Bs

W10/1K



No.
(%)
(%)
(%)
(%)
(T)
(T)
B50/Bs
(W/kg)
























COMPARATIVE
6-1
0
0
13
13
1.61
2.06
0.78
91


EXAMPLE











EXAMPLE
6-2
6
0.2
30
10
1.75
2.06
0.85
64


OF
6-3
43
1.8
33
8
1.75
2.06
0.85
56


PRESENT
6-4
78
6.2
33
8
1.75
2.06
0.85
43


INVENTION
6-5
100
38
33
8
1.75
2.06
0.85
38



6-6
100
68
33
8
1.75
2.06
0.85
43



6-7
100
87
33
8
1.75
2.06
0.85
58


COMPARATIVE
6-8
0
0
13
13
1.61
2.06
0.78
92


EXAMPLE











EXAMPLE
6-9
7
0.1
43
4.2
1.79
2.06
0.87
61


OF
6-10
65
2.4
54
1.8
1.85
2.06
0.90
52


PRESENT
6-11
85
5.9
54
1.8
1.85
2.06
0.90
43


INVENTION
6-12
100
46
54
1.8
1.85
2.06
0.90
32



6-13
100
72
54
1.8
1.85
2.06
0.90
35



6-14
100
90
54
1.8
1.85
2.06
0.90
52


COMPARATIVE
6-15
0
0
13
13
1.63
2.06
0.79
93


EXAMPLE











EXAMPLE
6-16
6
0.2
64
2.2
1.90
2.06
0.92
61


OF
6-17
76
3.5
80
0.9
1.98
2.06
0.96
46


PRESENT
6-18
92
8.2
80
0.9
1.98
2.06
0.96
40


INVENTION
6-19
100
38
80
0.9
1.98
2.06
0.96
28



6-20
100
69
80
0.9
1.98
2.06
0.96
32



6-21
100
85
80
0.9
1.98
2.06
0.96
48


COMPARATIVE
6-22
0
0
13
13
1.61
2.06
0.78
98


EXAMPLE











EXAMPLE
6-23
5
0.1
30
10
1.75
2.06
0.85
64


OF
6-24
68
2.2
31
9
1.73
2.06
0.84
59


PRESENT
6-25
84
6.4
31
9
1.73
2.06
0.84
44


INVENTION
6-26
100
35
31
9
1.73
2.06
0.84
39



6-27
100
71
31
9
1.73
2.06
0.84
43



6-28
100
95
31
9
1.73
2.06
0.84
59


COMPARATIVE
6-29
0
0
13
13
1.61
2.06
0.78
103


EXAMPLE











EXAMPLE
6-30
5
2
42
4.9
1.81
2.06
0.88
64


OF
6-31
48
1.5
55
2.3
1.87
2.06
0.91
52


PRESENT
6-32
77
6.2
55
2.3
1.87
2.06
0.91
41


INVENTION
6-33
100
40
55
2.3
1.87
2.06
0.91
34



6-34
100
71
55
2.3
1.87
2.06
0.91
38



6-35
100
93
55
2.3
1.87
2.06
0.91
54


COMPARATIVE
6-36
0
0
13
13
1.63
2.06
0.79
98


EXAMPLE











EXAMPLE
6-37
7
0.2
62
2.1
1.92
2.06
0.93
63


OF
6-38
57
1.9
74
0.3
1.96
2.06
0.95
46


PRESENT
6-39
79
7.6
74
0.3
1.96
2.06
0.95
42


INVENTION
6-40
100
43
74
0.3
1.96
2.06
0.95
29



6-41
100
74
74
0.3
1.96
2.06
0.95
32



6-42
100
86
74
0.3
1.96
2.06
0.95
47









As listed in Table 16, in examples of the present invention (conditions No. 6-2 to No 6-7, No. 6-9 to No. 6-14, No. 6-16 to No. 6-21, No. 6-23 to No. 6-28, No. 6-30 to No. 6-35, No. 6-37 to No. 6-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 17, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 17, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1k maintained a higher property level. Further, it could be confirmed that the core loss W10/1k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Seventh Experiment
In a seventh experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 7-1 to condition No. 7-42) were studied.
Base metal plates (silicon steel plates) used in the seventh experiment contained components of the composition Q listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the seventh experiment transformed to a γ single phase was 1020° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 7-1 to the condition No. 7-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 18.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Mo layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a sputtering method, except in the conditions No. 7-1, No. 7-8, No. 7-15, No. 7-22, No. 7-29, and No. 7-36. Thickness of each of the Mo layers (total thickness on the both surfaces) is listed in Table 18.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 18.









TABLE 18








BASE METAL PLATE













REDUCTION
DISLOCATION

METAL LAYER















CONDITION
COMPO-
RATE
DENSITY
THICKNESS

THICKNESS
















No.
SITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)

















COMPARATIVE
7-1
Q
WITHOUT
95
1 × 1015
100
NONE


EXAMPLE






















EXAMPLE
7-2
Q
WITHOUT
95
1 × 1015
100
Mo
2.4


OF
7-3
Q
WITHOUT
95
1 × 1015
100
Mo
2.4


PRESENT
7-4
Q
WITHOUT
95
1 × 1015
100
Mo
2.4


INVENTION
7-5
Q
WITHOUT
95
1 × 1015
100
Mo
2.4



7-6
Q
WITHOUT
95
1 × 1015
100
Mo
2.4



7-7
Q
WITHOUT
95
1 × 1015
100
Mo
2.4














COMPARATIVE
7-8
Q
WITHOUT
97.5
1 × 1016
100
NONE


EXAMPLE






















EXAMPLE
7-9
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4


OF
7-10
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4


PRESENT
7-11
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4


INVENTION
7-12
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4



7-13
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4



7-14
Q
WITHOUT
97.5
1 × 1016
100
Mo
2.4














COMPARATIVE
7-15
Q
WITH
95
8 × 1016
100
NONE


EXAMPLE






















EXAMPLE
7-16
Q
WITH
95
8 × 1016
100
Mo
2.4


OF
7-17
Q
WITH
95
8 × 1016
100
Mo
2.4


PRESENT
7-18
Q
WITH
95
8 × 1016
100
Mo
2.4


INVENTION
7-19
Q
WITH
95
8 × 1016
100
Mo
2.4



7-20
Q
WITH
95
8 × 1016
100
Mo
2.4



7-21
Q
WITH
95
8 × 1016
100
Mo
2.4














COMPARATIVE
7-22
Q
WITHOUT
95
1 × 1015
250
NONE


EXAMPLE






















EXAMPLE
7-23
Q
WITHOUT
95
1 × 1015
250
Mo
6


OF
7-24
Q
WITHOUT
95
1 × 1015
250
Mo
6


PRESENT
7-25
Q
WITHOUT
95
1 × 1015
250
Mo
6


INVENTION
7-26
Q
WITHOUT
95
1 × 1015
250
Mo
6



7-27
Q
WITHOUT
95
1 × 1015
250
Mo
6



7-28
Q
WITHOUT
95
1 × 1015
250
Mo
6














COMPARATIVE
7-29
Q
WITHOUT
97.5
1 × 1016
250
NONE


EXAMPLE






















EXAMPLE
7-30
Q
WITHOUT
97.5
1 × 1015
250
Mo
6


OF
7-31
Q
WITHOUT
97.5
1 × 1015
250
Mo
6


PRESENT
7-32
Q
WITHOUT
97.5
1 × 1015
250
Mo
6


INVENTION
7-33
Q
WITHOUT
97.5
1 × 1016
250
Mo
6



7-34
Q
WITHOUT
97.5
1 × 1016
250
Mo
6



7-35
Q
WITHOUT
97.5
1 × 1016
250
Mo
6














COMPARATIVE
7-36
Q
WITH
95
8 × 1016
250
NONE


EXAMPLE






















EXAMPLE
7-37
Q
WITH
95
8 × 1016
250
Mo
6


OF
7-38
Q
WITH
95
8 × 1015
250
Mo
6


PRESENT
7-39
Q
WITH
95
8 × 1016
250
Mo
6


INVENTION
7-40
Q
WITH
95
8 × 1016
250
Mo
6



7-41
Q
WITH
95
8 × 1016
250
Mo
6



7-42
Q
WITH
95
8 × 1016
250
Mo
6













FIRST SAMPLE












ACCUMULATION
ACCUMULATION
SECOND SAMPLE
















HETING
MEASURED
DEGREE OF
DEGREE OF
KEEPING
KEEPING



CONDITION
RATE
TEMPERATURE
[200] PLANE
[222] PLANE
TEMPERATURE
TIME



No.
(° C./s)
(° C.)
(%)
(%)
(° C.)
(s)





COMPARATIVE
7-1
5
1020
17
14
1100
2


EXAMPLE









EXAMPLE
7-2
5
1020
27
13
1020
2


OF
7-3
5
1020
27
13
1100
2


PRESENT
7-4
5
1020
27
13
1100
5


INVENTION
7-5
5
1020
27
13
1100
30



7-6
5
1020
27
13
1100
120



7-7
5
1020
27
13
1100
360


COMPARATIVE
7-8
5
1010
17
14
1100
2


EXAMPLE









EXAMPLE
7-9
5
1020
32
7
1020
2


OF
7-10
5
1020
32
7
1100
2


PRESENT
7-11
5
1020
32
7
1100
5


INVENTION
7-12
5
1020
32
7
1100
30



7-13
5
1020
32
7
1100
120



7-14
5
1020
32
7
1100
360


COMPARATIVE
7-15
5
1010
17
13
1100
2


EXAMPLE









EXAMPLE
7-16
5
1020
53
3.8
1020
2


OF
7-17
5
1020
53
3.8
1100
2


PRESENT
7-18
5
1020
53
3.8
1100
5


INVENTION
7-19
5
1020
53
3.8
1100
30



7-20
5
1020
53
3.8
1100
120



7-21
5
1020
53
3.8
1100
360


COMPARATIVE
7-22
5
1010
18
13
1150
2


EXAMPLE









EXAMPLE
7-23
5
1020
26
12
1020
2


OF
7-24
5
1020
26
12
1150
3


PRESENT
7-25
5
1020
26
12
1150
7


INVENTION
7-26
5
1020
26
12
1150
35



7-27
5
1020
26
12
1150
140



7-28
5
1020
26
12
1150
420


COMPARATIVE
7-29
5
1020
18
13
1150
2


EXAMPLE









EXAMPLE
7-30
5
1020
35
6
1020
2


OF
7-31
5
1020
35
6
1150
3


PRESENT
7-32
5
1020
35
6
1150
7


INVENTION
7-33
5
1020
35
6
1150
35



7-34
5
1020
35
6
1150
140



7-35
5
1020
35
6
1150
420


COMPARATIVE
7-36
5
1020
18
14
1150
2


EXAMPLE









EXAMPLE
7-37
5
1020
54
3.1
1020
2


OF
7-38
5
1020
54
3.1
1150
3


PRESENT
7-39
5
1020
54
3.1
1150
7


INVENTION
7-40
5
1020
54
3.1
1150
35



7-41
5
1020
54
3.1
1150
140



7-42
5
1020
54
3.1
1150
420













SECOND SAMPLE
THIRD SAMPLE
















ACCUMULATION
ACCUMULATION
COOL-

ACCUMULATION
ACCUMULATION




DEGREE OF
DEGREE OF
ING
DIS-
DEGREE OF
DEGREE OF



CONDITION
[200] PLANE
[222] PLANE
RATE
TANCE
[200] PLANE
[222] PLANE



No.
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
7-1
13
13
10
50
13
13


EXAMPLE









EXAMPLE
7-2
30
10
10
54
30
10


OF
7-3
30
10
10
54
30
10


PRESENT
7-4
30
10
10
54
30
10


INVENTION
7-5
30
10
10
54
30
10



7-6
30
10
10
54
30
10



7-7
30
10
10
54
30
10


COMPARATIVE
7-8
13
13
10
50
13
13


EXAMPLE









EXAMPLE
7-9
41
5.8
10
54
41
5.8


OF
7-10
52
2.2
10
54
52
2.2


PRESENT
7-11
52
2.2
10
54
52
2.2


INVENTION
7-12
52
2.2
10
54
52
2.2



7-13
52
2.2
10
54
52
2.2



7-14
52
2.2
10
54
52
2.2


COMPARATIVE
7-15
13
13
10
50
13
13


EXAMPLE









EXAMPLE
7-16
60
2.5
10
54
60
2.5


OF
7-17
76
1.3
10
54
76
1.3


PRESENT
7-18
76
1.3
10
54
76
1.3


INVENTION
7-19
76
1.3
10
54
76
1.3



7-20
76
1.3
10
54
76
1.3



7-21
76
1.3
10
54
76
1.3


COMPARATIVE
7-22
13
13
10
125
13
13


EXAMPLE









EXAMPLE
7-23
30
11
10
136
30
11


OF
7-24
32
8
10
136
32
8


PRESENT
7-25
32
8
10
136
32
8


INVENTION
7-26
32
8
10
136
32
8



7-27
32
8
10
136
32
8



7-28
32
8
10
136
32
8


COMPARATIVE
7-29
13
13
10
125
13
13


EXAMPLE









EXAMPLE
7-30
43
45
10
135
43
4.5


OF
7-31
53
2.4
10
136
53
2.4


PRESENT
7-32
53
2.4
10
136
53
2.4


INVENTION
7-33
53
2.4
10
136
53
2.4



7-34
53
2.4
10
136
53
2.4



7-35
53
2.4
10
136
53
2.4


COMPARATIVE
7-36
13
13
10
125
13
13


EXAMPLE









EXAMPLE
7-37
59
3.5
10
136
59
3.5


OF
7-38
70
0.4
10
136
70
0.4


PRESENT
7-39
70
0.4
10
136
70
0.4


INVENTION
7-40
70
0.4
10
136
70
0.4



7-41
70
0.4
10
136
70
0.4



7-42
70
0.4
10
136
70
0.4









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Mo content was 3.8 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 19.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 19.

















TABLE 19









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
7-1
0
0
13
13
1.60
2.05
0.78
91


EXAMPLE


EXAMPLE
7-2
8
0.2
30
10
1.74
2.05
0.85
62


OF
7-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
7-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
7-5
100
35
30
10
1.74
2.05
0.85
37



7-6
100
73
30
10
1.74
2.05
0.85
43



7-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
7-8
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
7-9
7
0.2
41
5.8
1.78
2.05
0.87
63


OF
7-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
7-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
7-12
100
42
53
2.7
1.85
2.05
0.90
33



7-13
100
71
53
2.7
1.85
2.05
0.90
38



7-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
7-15
0
0
13
13
1.62
2.05
0.79
93


EXAMPLE


EXAMPLE
7-16
7
0.3
60
2.5
1.91
2.05
0.93
61


OF
7-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
7-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
7-19
100
37
75
1.3
1.95
2.05
0.95
28



7-20
100
72
76
1.4
1.97
2.05
0.96
33



7-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
7-22
0
0
13
13
1.60
2.05
0.78
98


EXAMPLE


EXAMPLE
7-23
4
0.2
30
11
1.74
2.05
0.85
64


OF
7-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
7-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
7-26
100
45
32
9
1.74
2.05
0.85
37



7-27
100
72
32
9
1.74
2.05
0.85
42



7-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
7-29
0
0
13
13
1.60
2.05
0.78
100


EXAMPLE


EXAMPLE
7-30
8
0.2
43
4.5
1.78
2.05
0.87
64


OF
7-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
7-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
7-33
100
38
56
2.2
1.87
2.05
0.91
32



7-34
100
71
56
2.1
1.85
2.05
0.90
38



7-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
7-36
0
0
13
13
1.62
2.05
0.79
97


EXAMPLE


EXAMPLE
7-37
6
0.1
59
3.5
1.91
2.05
0.93
62


OF
7-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
7-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
7-40
100
41
82
0.8
1.97
2.05
0.96
26



7-41
100
76
82
0.8
1.95
2.05
0.95
32



7-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 18, in examples of the present invention (conditions No. 7-2 to No. 7-7, No. 7-9 to No. 7-14, No. 7-16 to No. 7-21, No. 7-23 to No. 7-28, No. 7-30 to No. 7-35, No. 7-37 to No. 7-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 19, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 19, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1k maintained a higher property level. Further, it could be confirmed that the core loss W10/1k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Eighth Experiment
In an eighth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 8-1 to condition No. 8-42) were studied.
Base metal plates (silicon steel plates) used in the eighth experiment contained components of the composition R listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the eighth experiment transformed to a γ single phase was 1010° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 8-1 to the condition No. 8-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 20.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, V layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by an sputtering method, except in the conditions No. 8-1, No. 8-8, No. 8-15, No. 8-22, No. 8-29, and No. 8-36. Thickness of each of the V layers (total thickness on the both surfaces) is listed in Table 20.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 20.









TABLE 20









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
8-1
R
WITHOUT
95
1 × 1015
100
NONE
50
1010
17


EXAMPLE


















EXAMPLE
8-2
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25


OF
8-3
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25


PRESENT
8-4
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25


INVENTION
8-5
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25



8-6
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25



8-7
R
WITHOUT
95
1 × 1015
100
V
4
50
1010
25

















COMPARATIVE
8-8
R
WITHOUT
97.5
1 × 1016
100
NONE
50
1010
17


EXAMPLE


















EXAMPLE
8-9
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31


OF
8-10
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31


PRESENT
8-11
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31


INVENTION
8-12
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31



8-13
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31



8-14
R
WITHOUT
97.5
1 × 1016
100
V
4
50
1010
31

















COMPARATIVE
8-15
R
WITH
95
8 × 1016
100
NONE
50
1010
17


EXAMPLE


















EXAMPLE
8-16
R
WITH
95
8 × 1016
100
V
4
50
1010
48


OF
8-17
R
WITH
95
8 × 1016
100
V
4
50
1010
48


PRESENT
8-18
R
WITH
95
8 × 1016
100
V
4
50
1010
48


INVENTION
8-19
R
WITH
95
8 × 1016
100
V
4
50
1010
48



8-20
R
WITH
95
8 × 1016
100
V
4
50
1010
48



8-21
R
WITH
95
8 × 1016
100
V
4
50
1010
48

















COMPARATIVE
8-22
R
WITHOUT
95
1 × 1015
250
NONE
50
1010
17


EXAMPLE


















EXAMPLE
8-23
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27


OF
8-24
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27


PRESENT
8-25
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27


INVENTION
8-26
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27



8-27
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27



8-28
R
WITHOUT
95
1 × 1015
250
V
10
50
1010
27

















COMPARATIVE
8-29
R
WITHOUT
97.5
1 × 1016
250
NONE
50
1010
18


EXAMPLE


















EXAMPLE
8-30
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33


OF
8-31
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33


PRESENT
8-32
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33


INVENTION
8-33
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33



8-34
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33



8-35
R
WITHOUT
97.5
1 × 1016
250
V
10
50
1010
33

















COMPARATIVE
8-36
R
WITH
95
8 × 1016
250
NONE
50
1010
17


EXAMPLE


















EXAMPLE
8-37
R
WITH
95
8 × 1016
250
V
10
50
1010
53


OF
8-38
R
WITH
95
8 × 1016
250
V
10
50
1010
53


PRESENT
8-39
R
WITH
95
8 × 1016
250
V
10
50
1010
53


INVENTION
8-40
R
WITH
95
8 × 1016
250
V
10
50
1010
53



8-41
R
WITH
95
8 × 1016
250
V
10
50
1010
53



8-42
R
WITH
95
8 × 1016
250
V
10
50
1010
53














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
8-1
13
1050
2
13
13
10
50
13
13


EXAMPLE


EXAMPLE
8-2
16
1010
2
30
12
10
54
30
12


OF
8-3
16
1050
2
32
8
10
54
32
8


PRESENT
8-4
16
1050
5
32
8
10
54
32
8


INVENTION
8-5
16
1050
30
32
8
10
54
32
8



8-6
16
1050
120
32
8
10
54
32
8



8-7
16
1050
360
32
8
10
54
32
8


COMPARATIVE
8-8
12
1050
2
13
13
10
50
13
13


EXAMPLE


EXAMPLE
8-9
6
1010
2
42
5.8
10
54
42
5.8


OF
8-10
6
1050
2
51
2.8
10
54
51
2.8


PRESENT
8-11
6
1050
5
51
2.8
10
54
51
2.8


INVENTION
8-12
6
1050
30
51
2.8
10
54
51
2.8



8-13
6
1050
120
51
2.8
10
54
51
2.8



8-14
6
1050
360
51
2.8
10
54
51
2.8


COMPARATIVE
8-15
12
1050
2
13
13
10
50
13
13


EXAMPLE


EXAMPLE
8-16
4.8
1010
2
59
3.1
10
54
59
3.1


OF
8-17
4.8
1050
2
73
1.6
10
54
73
1.6


PRESENT
8-18
4.8
1050
5
73
1.6
10
54
73
1.6


INVENTION
8-19
4.8
1050
30
73
1.6
10
54
73
1.6



8-20
4.8
1050
120
73
1.6
10
54
73
1.6



8-21
4.8
1050
360
73
1.6
10
54
73
1.6


COMPARATIVE
8-22
13
1100
2
13
13
10
125
13
13


EXAMPLE


EXAMPLE
8-23
11
1010
2
30
11
10
136
30
11


OF
8-24
11
1100
3
31
10
10
136
31
10


PRESENT
8-25
11
1100
7
31
10
10
136
31
10


INVENTION
8-26
11
1100
35
31
10
10
136
31
10



8-27
11
1100
140
31
10
10
136
31
10



8-28
11
1100
420
31
10
10
136
31
10


COMPARATIVE
8-29
13
1100
2
13
13
10
125
13
13


EXAMPLE


EXAMPLE
8-30
7
1010
2
43
5.1
10
136
43
5.1


OF
8-31
7
1100
3
58
1.7
10
136
58
1.7


PRESENT
8-32
7
1100
7
58
1.7
10
136
58
1.7


INVENTION
8-33
7
1100
35
58
1.7
10
136
58
1.7



8-34
7
1100
140
58
1.7
10
136
58
1.7



8-35
7
1100
420
58
1.7
10
136
58
1.7


COMPARATIVE
8-36
12
1100
2
13
13
10
125
13
13


EXAMPLE


EXAMPLE
8-37
3.9
1010
2
62
2.1
10
136
62
2.1


OF
8-38
3.9
1100
3
76
0.5
10
136
76
0.5


PRESENT
8-39
3.9
1100
7
76
0.5
10
136
76
0.5


INVENTION
8-40
3.9
1100
35
76
0.5
10
136
76
0.5



8-41
3.9
1100
140
76
0.5
10
136
76
0.5



8-42
3.9
1100
420
76
0.5
10
136
76
0.5









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the V content was 1.8 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 21.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 21.

















TABLE 21









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
8-1
0
0
13
13
1.60
2.05
0.78
91


EXAMPLE


EXAMPLE
8-2
8
0.2
30
12
1.74
2.05
0.85
62


OF
8-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
8-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
8-5
100
35
30
10
1.74
2.05
0.85
37



8-6
100
73
30
10
1.74
2.05
0.85
43



8-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
8-8
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
8-9
6
0.2
42
5.8
1.76
2.05
0.86
61


OF
8-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
8-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
8-12
100
42
53
2.7
1.85
2.05
0.90
33



8-13
100
71
53
2.7
1.85
2.05
0.90
38



8-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
8-15
0
0
13
13
1.62
2.05
0.79
94


EXAMPLE


EXAMPLE
8-16
7
0.3
59
3.1
1.89
2.05
0.92
62


OF
8-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
8-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
8-19
100
37
75
1.3
1.95
2.05
0.95
28



8-20
100
72
76
1.4
1.97
2.05
0.96
33



8-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
8-22
0
0
13
13
1.60
2.05
0.78
103


EXAMPLE


EXAMPLE
8-23
5
0.1
30
11
1.74
2.05
0.85
63


OF
8-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
8-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
8-26
100
45
32
9
1.74
2.05
0.85
37



8-27
100
74
32
9
1.74
2.05
0.85
42



8-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
8-29
0
0
13
13
1.60
2.05
0.78
102


EXAMPLE


EXAMPLE
8-30
8
0.3
43
5.1
1.78
2.05
0.87
63


OF
8-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
8-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
8-33
100
38
56
2.2
1.87
2.05
0.91
32



8-34
100
71
56
2.1
1.85
2.05
0.90
38



8-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
8-36
0
0
13
13
1.62
2.05
0.79
99


EXAMPLE


EXAMPLE
8-37
5
0.1
62
2.1
1.89
2.05
0.92
62


OF
8-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
8-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
8-40
100
41
82
0.8
1.97
2.05
0.96
26



8-41
100
76
82
0.8
1.95
2.05
0.95
32



8-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 20, in examples of the present invention (conditions No. 8-2 to No. 8-7, No. 8-9 to No. 8-14, No. 8-16 to No. 8-21, No. 8-23 to No. 8-28, No. 8-30 to No. 8-35, No. 8-37 to No. 8-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 21, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 21, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1k maintained a higher property level. Further, it could be confirmed that the core loss W10/1k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Ninth Experiment
In a ninth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 9-1 to condition No. 9-42) were studied.
Base metal plates (silicon steel plates) used in the ninth experiment contained components of the composition S listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the ninth experiment transformed to a γ single phase was 1080° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 9-1 to the condition No. 9-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 22.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Cr layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by an electroplating method, except in the conditions No. 9-1, No. 9-8, No. 9-15, No. 9-22, No. 9-29, and No. 9-36. Thickness of each of the Cr layers (total thickness on the both surfaces) is listed in Table 22.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 22.









TABLE 22









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
9-1
S
WITHOUT
95
1 × 1015
100
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-2
S
WITHOUT
95
1 × 1015
100
Cr
3
50
1080
27


OF
9-3
S
WITHOUT
95
1 × 1015
100
Cr
3
50
1080
27


PRESENT
9-4
S
WITHOUT
95
1 × 1015
100
Cr
3
50
1080
27


INVENTION
9-5
S
WITHOUT
95
1 × 1016
100
Cr
3
50
1080
27



9-6
S
WITHOUT
95
1 × 1015
100
Cr
3
50
1080
27



9-7
S
WITHOUT
95
1 × 1015
100
Cr
3
50
1080
27

















COMPARATIVE
9-8
S
WITHOUT
97.5
1 × 1016
100
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-9
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32


OF
9-10
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32


PRESENT
9-11
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32


INVENTION
9-12
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32



9-13
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32



9-14
S
WITHOUT
97.5
1 × 1016
100
Cr
3
50
1080
32

















COMPARATIVE
9-15
S
WITH
95
8 × 1016
100
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-16
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58


OF
9-17
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58


PRESENT
9-18
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58


INVENTION
9-19
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58



9-20
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58



9-21
S
WITH
95
8 × 1016
100
Cr
3
50
1080
58

















COMPARATIVE
9-22
S
WITHOUT
95
1 × 1015
250
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-23
S
WITHOUT
95
1 × 1015
250
Cr
8
50
1080
25


OF
9-24
S
WITHOUT
95
1 × 1015
250
Cr
8
50
1080
25


PRESENT
9-25
S
WITHOUT
95
1 × 1016
250
Cr
8
50
1080
25


INVENTION
9-26
S
WITHOUT
95
1 × 1015
250
Cr
8
50
1080
25



9-27
S
WITHOUT
95
1 × 1015
250
Cr
8
50
1080
25



9-28
S
WITHOUT
95
1 × 1015
250
Cr
8
50
1080
25

















COMPARATIVE
9-29
S
WITHOUT
97.5
1 × 1016
250
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-30
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35


OF
9-31
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35


PRESENT
9-32
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35


INVENTION
9-33
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35



9-34
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35



9-35
S
WITHOUT
97.5
1 × 1016
250
Cr
8
50
1080
35

















COMPARATIVE
9-36
S
WITH
95
8 × 1016
250
NONE
50
1080
16


EXAMPLE


















EXAMPLE
9-37
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52


OF
9-38
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52


PRESENT
9-39
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52


INVENTION
9-40
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52



9-41
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52



9-42
S
WITH
95
8 × 1016
250
Cr
8
50
1080
52














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
9-1
13
1080
2
13
13
50
50
13
13


EXAMPLE


EXAMPLE
9-2
13
1080
2
30
10
50
54
30
10


OF
9-3
13
1130
2
30
11
50
54
30
11


PRESENT
9-4
13
1130
5
30
11
50
54
30
11


INVENTION
9-5
13
1130
30
30
11
50
54
30
11



9-6
13
1130
120
30
11
50
54
30
11



9-7
13
1130
360
30
11
50
54
30
11


COMPARATIVE
9-8
13
1130
2
13
13
50
50
13
13


EXAMPLE


EXAMPLE
9-9
5
1080
2
46
4.8
50
54
46
4.8


OF
9-10
5
1130
2
57
2.1
50
54
57
2.1


PRESENT
9-11
5
1130
5
57
2.1
50
54
57
2.1


INVENTION
9-12
5
1130
30
57
2.1
50
54
57
2.1



9-13
5
1130
120
57
2.1
50
54
57
2.1



9-14
5
1130
360
57
2.1
50
54
57
2.1


COMPARATIVE
9-15
13
1130
2
13
13
50
50
13
13


EXAMPLE


EXAMPLE
9-16
3.1
1080
2
61
2.3
50
54
61
2.3


OF
9-17
3.1
1130
2
81
0.8
50
54
81
0.8


PRESENT
9-18
3.1
1130
5
81
0.8
50
54
81
0.8


INVENTION
9-19
3.1
1130
30
81
0.8
50
54
81
0.8



9-20
3.1
1130
120
81
0.8
50
54
81
0.8



9-21
3.1
1130
360
81
0.8
50
54
81
0.8


COMPARATIVE
9-22
13
1180
2
13
13
50
125
13
13


EXAMPLE


EXAMPLE
9-23
12
1080
2
30
12
50
136
30
12


OF
9-24
12
1180
3
33
7
50
136
33
7


PRESENT
9-25
12
1180
7
33
7
50
136
33
7


INVENTION
9-26
12
1180
35
33
7
50
136
33
7



9-27
12
1180
140
33
7
50
136
33
7



9-28
12
1180
420
33
7
50
136
33
7


COMPARATIVE
9-29
13
1180
2
13
13
50
125
13
13


EXAMPLE


EXAMPLE
9-30
6
1080
2
42
5.2
50
136
42
5.2


OF
9-31
6
1180
3
53
2.3
50
136
53
2.3


PRESENT
9-32
6
1180
7
53
2.3
50
136
53
2.3


INVENTION
9-33
6
1180
35
53
2.3
50
136
53
2.3



9-34
6
1180
140
53
2.3
50
136
53
2.3



9-35
6
1180
420
53
2.3
50
136
53
2.3


COMPARATIVE
9-36
13
1180
2
13
13
50
125
13
13


EXAMPLE


EXAMPLE
9-37
4.2
1080
2
62
2
50
136
62
2


OF
9-38
4.2
1180
3
74
0.9
50
136
74
0.9


PRESENT
9-39
4.2
1180
7
74
0.9
50
136
74
0.9


INVENTION
9-40
4.2
1180
35
74
0.9
50
136
74
0.9



9-41
4.2
1180
140
74
0.9
50
136
74
0.9



9-42
4.2
1180
420
74
0.9
50
136
74
0.9









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Cr content was 13.0 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 23.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 23.

















TABLE 23









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
9-1
0
0
13
13
1.60
2.05
0.78
95


EXAMPLE


EXAMPLE
9-2
6
0.2
30
10
1.74
2.05
0.85
62


OF
9-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
9-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
9-5
100
35
30
10
1.74
2.05
0.85
37



9-6
100
73
30
10
1.74
2.05
0.85
43



9-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
9-8
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
9-9
10
0.4
46
4.8
1.78
2.05
0.87
61


OF
9-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
9-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
9-12
100
42
53
2.7
1.85
2.05
0.90
33



9-13
100
71
53
2.7
1.85
2.05
0.90
38



9-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
9-15
0
0
13
13
1.62
2.05
0.79
94


EXAMPLE


EXAMPLE
9-16
9
0.3
61
2.3
1.89
2.05
0.92
62


OF
9-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
9-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
9-19
100
37
75
1.3
1.95
2.05
0.95
28



9-20
100
72
76
1.4
1.97
2.05
0.96
33



9-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
9-22
0
0
13
13
1.60
2.05
0.78
98


EXAMPLE


EXAMPLE
9-23
6
0.2
30
12
1.74
2.05
0.85
65


OF
9-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
9-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
9-26
100
45
32
9
1.74
2.05
0.85
37



9-27
100
72
32
9
1.74
2.05
0.85
42



9-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
9-29
0
0
13
13
1.60
2.05
0.78
96


EXAMPLE


EXAMPLE
9-30
5
0.1
42
5.2
1.78
2.05
0.87
64


OF
9-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
9-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
9-33
100
38
56
2.2
1.87
2.05
0.91
32



9-34
100
71
56
2.1
1.85
2.05
0.90
38



9-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
9-36
0
0
13
13
1.62
2.05
0.79
100


EXAMPLE


EXAMPLE
9-37
5
0.1
62
2
1.89
2.05
0.92
64


OF
9-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
9-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
9-40
100
41
82
0.8
1.97
2.05
0.96
26



9-41
100
76
82
0.8
1.95
2.05
0.95
32



9-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 22, in examples of the present invention (conditions No. 9-2 to No. 9-7, No. 9-9 to No. 9-14, No. 9-16 to No. 9-21, No. 9-23 to No. 9-28, No. 9-30 to No. 9-35, No. 9-37 to No. 9-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 23, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 23, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1 k maintained a higher property level. Further, it could be confirmed that the core loss W10/1 k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Tenth Experiment
In a tenth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 10-1 to condition No. 10-42) were studied.
Base metal plates (silicon steel plates) used in the tenth experiment contained components of the composition T listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the tenth experiment transformed to a γ single phase was 1020° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 10-1 to the condition No. 10-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 24.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Ti layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a sputtering method, except in the conditions No. 10-1, No. 10-8, No. 10-15, No. 10-22, No. 10-29, and No. 10-36. Thickness of each of the Ti layers (total thickness on the both surfaces) is listed in Table 24.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes of the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 24.









TABLE 24









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
10-1
T
WITHOUT
95
1 × 1015
100
NONE
50
1020
17


EXAMPLE


















EXAMPLE
10-2
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25


OF
10-3
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25


PRESENT
10-4
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25


INVENTION
10-5
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25



10-6
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25



10-7
T
WITHOUT
95
1 × 1015
100
Ti
5
50
1020
25

















COMPARATIVE
10-8
T
WITHOUT
97.5
1 × 1016
100
NONE
50
1020
17


EXAMPLE


















EXAMPLE
10-9
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35


OF
10-10
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35


PRESENT
10-11
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35


INVENTION
10-12
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35



10-13
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35



10-14
T
WITHOUT
97.5
1 × 1016
100
Ti
5
50
1020
35

















COMPARATIVE
10-15
T
WITH
95
8 × 1016
100
NONE
50
1020
16


EXAMPLE


















EXAMPLE
10-16
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61


OF
10-17
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61


PRESENT
10-18
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61


INVENTION
10-19
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61



10-20
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61



10-21
T
WITH
95
8 × 1016
100
Ti
5
50
1020
61

















COMPARATIVE
10-22
T
WITHOUT
95
1 × 1015
250
NONE
50
1020
17


EXAMPLE


















EXAMPLE
10-23
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26


OF
10-24
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26


PRESENT
10-25
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26


INVENTION
10-26
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26



10-27
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26



10-28
T
WITHOUT
95
1 × 1015
250
Ti
13
50
1020
26

















COMPARATIVE
10-29
T
WITHOUT
97.5
1 × 1016
250
NONE
50
1020
17


EXAMPLE


















EXAMPLE
10-30
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38


OF
10-31
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38


PRESENT
10-32
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38


INVENTION
10-33
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38



10-34
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38



10-35
T
WITHOUT
97.5
1 × 1016
250
Ti
13
50
1020
38

















COMPARATIVE
10-36
T
WITH
95
8 × 1016
250
NONE
50
1020
18


EXAMPLE


















EXAMPLE
10-37
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58


OF
10-38
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58


PRESENT
10-39
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58


INVENTION
10-40
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58



10-41
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58



10-42
T
WITH
95
8 × 1016
250
Ti
13
50
1020
58














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
10-1
13
1050
2
13
13
8
50
13
13


EXAMPLE


EXAMPLE
10-2
16
1020
2
30
11
8
54
30
11


OF
10-3
16
1050
2
33
9
8
54
33
9


PRESENT
10-4
16
1050
5
33
9
8
54
33
9


INVENTION
10-5
16
1050
30
33
9
8
54
33
9



10-6
16
1050
120
33
9
8
54
33
9



10-7
16
1050
360
33
9
8
54
33
9


COMPARATIVE
10-8
13
1050
2
13
13
8
50
13
13


EXAMPLE


EXAMPLE
10-9
4
1020
2
41
5.8
8
54
41
5.8


OF
10-10
4
1050
2
52
3.2
8
54
52
3.2


PRESENT
10-11
4
1050
5
52
3.2
8
54
52
3.2


INVENTION
10-12
4
1050
30
52
3.2
8
54
52
3.2



10-13
4
1050
120
52
3.2
8
54
52
3.2



10-14
4
1050
360
52
3.2
8
54
52
3.2


COMPARATIVE
10-15
14
1050
2
13
13
8
50
13
13


EXAMPLE


EXAMPLE
10-16
2.7
1020
2
64
1.8
8
54
64
1.8


OF
10-17
2.7
1050
2
76
1.2
8
54
76
1.2


PRESENT
10-18
2.7
1050
5
76
1.2
8
54
76
1.2


INVENTION
10-19
2.7
1050
30
76
1.2
8
54
76
1.2



10-20
2.7
1050
120
76
1.2
8
54
76
1.2



10-21
2.7
1050
360
76
1.2
8
54
76
1.2


COMPARATIVE
10-22
14
1100
2
13
13
8
125
13
13


EXAMPLE


EXAMPLE
10-23
13
1020
2
30
11
8
136
30
11


OF
10-24
13
1100
3
32
11
8
136
32
11


PRESENT
10-25
13
1100
7
32
11
8
136
32
11


INVENTION
10-26
13
1100
35
32
11
8
136
32
11



10-27
13
1100
140
32
11
8
136
32
11



10-28
13
1100
420
32
11
8
136
32
11


COMPARATIVE
10-29
14
1100
2
13
13
8
125
13
13


EXAMPLE


EXAMPLE
10-30
4
1020
2
42
4.2
8
136
42
4.2


OF
10-31
4
1100
3
54
2.9
8
136
54
2.9


PRESENT
10-32
4
1100
7
54
2.9
8
136
54
2.9


INVENTION
10-33
4
1100
35
54
2.9
8
136
54
2.9



10-34
4
1100
140
54
2.9
8
136
54
2.9



10-35
4
1100
420
54
2.9
8
136
54
2.9


COMPARATIVE
10-36
13
1100
2
13
13
8
125
13
13


EXAMPLE


EXAMPLE
10-37
3.4
1020
2
63
1.8
8
136
63
1.8


OF
10-38
3.4
1100
3
80
0.7
8
136
80
0.7


PRESENT
10-39
3.4
1100
7
80
0.7
8
136
80
0.7


INVENTION
10-40
3.4
1100
35
80
0.7
8
136
80
0.7



10-41
3.4
1100
140
80
0.7
8
136
80
0.7



10-42
3.4
1100
420
80
0.7
8
136
80
0.7









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Ti content was 1.2 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 25.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density 50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1 k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 25.

















TABLE 25









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
10-1
0
0
13
13
1.60
2.05
0.78
91


EXAMPLE


EXAMPLE
10-2
6
0.2
30
11
1.74
2.05
0.85
62


OF
10-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
10-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
10-5
100
35
30
10
1.74
2.05
0.85
37



10-6
100
73
30
10
1.74
2.05
0.85
43



10-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
10-8
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
10-9
8
0.2
41
5.8
1.76
2.05
0.86
62


OF
10-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
10-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
10-12
100
42
53
2.7
1.85
2.05
0.90
33



10-13
100
71
53
2.7
1.85
2.05
0.90
38



10-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
10-15
0
0
13
13
1.62
2.05
0.79
92


EXAMPLE


EXAMPLE
10-16
7
0.3
64
1.8
1.91
2.05
0.93
61


OF
10-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
10-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
10-19
100
37
75
1.3
1.95
2.05
0.95
28



10-20
100
72
76
1.4
1.97
2.05
0.96
33



10-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
10-22
0
0
13
13
1.60
2.05
0.78
102


EXAMPLE


EXAMPLE
10-23
8
0.3
30
11
1.74
2.05
0.85
65


OF
10-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
10-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
10-26
100
45
32
9
1.74
2.05
0.85
37



10-27
100
72
32
9
1.74
2.05
0.85
42



10-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
10-29
0
0
13
13
1.60
2.05
0.78
99


EXAMPLE


EXAMPLE
10-30
5
0.1
42
4.2
1.78
2.05
0.87
65


OF
10-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
10-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
10-33
100
38
56
2.2
1.87
2.05
0.91
32



10-34
100
71
56
2.1
1.85
2.05
0.90
38



10-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
10-36
0
0
13
13
1.62
2.05
0.79
97


EXAMPLE


EXAMPLE
10-37
4
0.1
63
1.8
1.91
2.05
0.93
62


OF
10-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
10-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
10-40
100
41
82
0.8
1.97
2.05
0.96
26



10-41
100
76
82
0.8
1.95
2.05
0.95
32



10-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 24, in examples of the present invention (conditions No. 10-2 to No. 10-7, No. 10-9 to No. 10-14, No. 10-16 to No. 10-21, No. 10-23 to No. 10-28, No. 10-30 to No. 10-35, No. 10-37 to No. 10-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 25, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 25, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1 k maintained a higher property level. Further, it could be confirmed that the core loss W10/1 k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Eleventh Experiment
In an eleventh experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 11-1 to condition No. 11-42) were studied.
Base metal plates (silicon steel plates) used in the eleventh experiment contained components of the composition U listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the eleventh experiment transformed to a γ single phase was 1000° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 11-1 to the condition No. 11-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 26.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, and it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Ga layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a vapor deposition method, except in the conditions No. 11-1, No. 11-8, No. 11-15, No. 11-22, No. 11-29, and No. 11-36. Thickness of each of the Ga layers (total thickness on the both surfaces) is listed in Table 26.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 26.









TABLE 26









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
11-1
U
WITHOUT
95
1 × 1015
100
NONE
10
1000
16


EXAMPLE


















EXAMPLE
11-2
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25


OF
11-3
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25


PRESENT
11-4
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25


INVENTION
11-5
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25



11-6
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25



11-7
U
WITHOUT
95
1 × 1015
100
Ge
6
10
1000
25

















COMPARATIVE
11-8
U
WITHOUT
97.5
1 × 1016
100
NONE
10
1000
16


EXAMPLE


















EXAMPLE
11-9
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38


OF
11-10
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38


PRESENT
11-11
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38


INVENTION
11-12
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38



11-13
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38



11-14
U
WITHOUT
97.5
1 × 1016
100
Ge
6
10
1000
38

















COMPARATIVE
11-15
U
WITH
95
8 × 1016
100
NONE
10
1000
17


EXAMPLE


















EXAMPLE
11-16
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48


OF
11-17
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48


PRESENT
11-18
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48


INVENTION
11-19
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48



11-20
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48



11-21
U
WITH
95
8 × 1016
100
Ge
6
10
1000
48

















COMPARATIVE
11-22
U
WITHOUT
95
1 × 1015
250
NONE
10
1000
17


EXAMPLE


















EXAMPLE
11-23
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26


OF
11-24
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26


PRESENT
11-25
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26


INVENTION
11-26
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26



11-27
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26



11-28
U
WITHOUT
95
1 × 1015
250
Ge
14
10
1000
26

















COMPARATIVE
11-29
U
WITHOUT
97.5
1 × 1016
250
NONE
10
1000
17


EXAMPLE


















EXAMPLE
11-30
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35


OF
11-31
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35


PRESENT
11-32
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35


INVENTION
11-33
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35



11-34
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35



11-35
U
WITHOUT
97.5
1 × 1016
250
Ge
14
10
1000
35

















COMPARATIVE
11-36
U
WITH
95
8 × 1016
250
NONE
10
1000
17


EXAMPLE


















EXAMPLE
11-37
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54


OF
11-38
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54


PRESENT
11-39
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54


INVENTION
11-40
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54



11-41
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54



11-42
U
WITH
95
8 × 1016
250
Ge
14
10
1000
54














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
11-1
13
1050
2
13
13
20
50
13
13


EXAMPLE


EXAMPLE
11-2
17
1000
2
30
10
20
54
30
10


OF
11-3
17
1050
2
32
10
20
54
32
10


PRESENT
11-4
17
1050
5
32
10
20
54
32
10


INVENTION
11-5
17
1050
30
32
10
20
54
32
10



11-6
17
1050
120
32
10
20
54
32
10



11-7
17
1050
360
32
10
20
54
32
10


COMPARATIVE
11-8
13
1050
2
13
13
20
50
13
13


EXAMPLE


EXAMPLE
11-9
9
1000
2
42
4.8
20
54
42
4.6


OF
11-10
9
1050
2
55
2.6
20
54
55
2.6


PRESENT
11-11
9
1050
5
55
2.6
20
54
55
2.6


INVENTION
11-12
9
1050
30
55
2.6
20
54
55
2.6



11-13
9
1050
120
55
2.6
20
54
55
2.6



11-14
9
1050
350
55
2.6
20
54
55
2.6


COMPARATIVE
11-15
13
1050
2
13
13
20
50
13
13


EXAMPLE


EXAMPLE
11-16
2.1
1000
2
59
2.9
20
54
59
2.9


OF
11-17
2.1
1050
2
74
1.5
20
54
74
1.5


PRESENT
11-18
2.1
1050
5
74
1.5
20
54
74
1.5


INVENTION
11-19
2.1
1050
30
74
1.5
20
54
74
1.5



11-20
2.1
1050
120
74
1.5
20
54
74
1.5



11-21
2.1
1050
360
74
1.5
20
54
74
1.5


COMPARATIVE
11-22
13
1100
2
13
13
20
125
13
13


EXAMPLE


EXAMPLE
11-23
15
1000
2
30
11
20
136
30
11


OF
11-24
15
1100
3
31
13
20
136
31
13


PRESENT
11-25
15
1100
7
31
13
20
136
31
13


INVENTION
11-26
15
1100
35
31
13
20
136
31
13



11-27
15
1100
140
31
13
20
136
31
13



11-28
15
1100
420
31
13
20
136
31
13


COMPARATIVE
11-29
14
1100
2
13
13
20
125
13
13


EXAMPLE


EXAMPLE
11-30
8
1000
2
45
4.2
20
136
45
4.2


OF
11-31
8
1100
3
52
3.2
20
136
52
3.2


PRESENT
11-32
8
1100
7
52
3.2
20
136
52
3.2


INVENTION
11-33
8
1100
35
52
3.2
20
136
52
3.2



11-34
8
1100
140
52
3.2
20
136
52
3.2



11-35
8
1100
420
52
3.2
20
136
52
3.2


COMPARATIVE
11-36
12
1100
2
13
13
20
125
13
13


EXAMPLE


EXAMPLE
11-37
3.4
1000
2
58
3
20
136
58
3


OF
11-38
3.4
1100
3
78
0.8
20
136
78
0.8


PRESENT
11-39
3.4
1100
7
78
0.8
20
136
78
0.8


INVENTION
11-40
3.4
1100
35
78
0.8
20
136
78
0.8



11-41
3.4
1100
140
78
0.8
20
136
78
0.8



11-42
3.4
1100
420
78
0.8
20
136
78
0.8









Further, an alloying ratio of the metal layer and a ratio of the α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Ga content was 4.1 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 27.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1 k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 27.

















TABLE 27









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
11-1
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
11-2
5
0.1
30
10
1.74
2.05
0.85
63


OF
11-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
11-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
11-5
100
35
30
10
1.74
2.05
0.85
37



11-6
100
73
30
10
1.74
2.05
0.85
43



11-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
11-8
0
0
13
13
1.60
2.05
0.78
92


EXAMPLE


EXAMPLE
11-9
8
0.2
42
4.8
1.78
2.05
0.87
62


OF
11-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
11-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
11-12
100
42
53
2.7
1.85
2.05
0.90
33



11-13
100
71
53
2.7
1.85
2.05
0.90
38



11-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
11-15
0
0
13
13
1.62
2.05
0.79
92


EXAMPLE


EXAMPLE
11-16
5
0.2
59
2.9
1.87
2.05
0.91
63


OF
11-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
11-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
11-19
100
37
75
1.3
1.95
2.05
0.95
28



11-20
100
72
76
1.4
1.97
2.05
0.96
33



11-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
11-22
0
0
13
13
1.60
2.05
0.78
101


EXAMPLE


EXAMPLE
11-23
4
0.2
30
11
1.74
2.05
0.85
64


OF
11-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
11-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
11-26
100
45
32
9
1.74
2.05
0.85
37



11-27
100
72
32
9
1.74
2.05
0.85
42



11-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
11-29
0
0
13
13
1.60
2.05
0.78
97


EXAMPLE


EXAMPLE
11-30
9
0.4
45
4.2
1.80
2.05
0.88
63


OF
11-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
11-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
11-33
100
38
56
2.2
1.87
2.05
0.91
32



11-34
100
71
56
2.1
1.85
2.05
0.90
38



11-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
11-36
0
0
13
13
1.62
2.05
0.79
100


EXAMPLE


EXAMPLE
11-37
9
0.2
58
3
1.91
2.05
0.93
64


OF
11-38
70
2.3
82
0.8
1.95
2.05
0.95
48


PRESENT
11-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
11-40
100
41
82
0.8
1.97
2.05
0.96
26



11-41
100
76
82
0.8
1.95
2.05
0.95
32



11-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 26, in examples of the present invention (conditions No. 11-2 to No. 11-7, No. 11-9 to No. 11-14, No. 11-16 to No. 11-21, No. 11-23 to No. 11-28, No. 11-30 to No. 11-35, No. 11-37 to No. 11-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 27, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 27, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1 k maintained a higher property level. Further, it could be confirmed that the core loss W10/1 k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Twelfth Experiment
In a twelfth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 12-1 to condition No. 12-42) were studied.
Base metal plates (silicon steel plates) used in the twelfth experiment contained components of the composition V listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the twelfth experiment transformed to a γ single phase was 1000° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 12-1 to the condition No. 12-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 28.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, Ge layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a sputtering method, except in the conditions No. 12-1, No. 12-8, No. 12-15, No. 12-22, No. 12-29, and No. 12-36. Thickness of each of the Ga layers (total thickness on the both surfaces) is listed in Table 28.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 28.









TABLE 28









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
12-1
V
WITHOUT
95
1 × 1015
100
NONE
10
1000
17


EXAMPLE


















EXAMPLE
12-2
V
WITHOUT
95
1 × 1015
100
Ge
7
10
1000
26


OF
12-3
V
WITHOUT
95
1 × 1016
100
Ge
7
10
1000
26


PRESENT
12-4
V
WITHOUT
95
1 × 1015
100
Ge
7
10
1000
26


INVENTION
12-5
V
WITHOUT
95
1 × 1015
100
Ge
7
10
1000
26



12-6
V
WITHOUT
95
1 × 1015
100
Ge
7
10
1000
26



12-7
V
WITHOUT
95
1 × 1015
100
Ge
7
10
1000
26

















COMPARATIVE
12-8
V
WITHOUT
97.5
1 × 1016
100
NONE
10
1000
18


EXAMPLE


















EXAMPLE
12-9
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39


OF
12-10
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39


PRESENT
12-11
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39


INVENTION
12-12
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39



12-13
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39



12-14
V
WITHOUT
97.5
1 × 1016
100
Ge
7
10
1000
39

















COMPARATIVE
12-15
V
WITH
95
8 × 1016
100
NONE
10
1000
17


EXAMPLE


















EXAMPLE
12-16
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58


OF
12-17
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58


PRESENT
12-18
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58


INVENTION
12-19
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58



12-20
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58



12-21
V
WITH
95
8 × 1016
100
Ge
7
10
1000
58

















COMPARATIVE
12-22
V
WITHOUT
95
1 × 1015
250
NONE
10
1000
17


EXAMPLE


















EXAMPLE
12-23
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27


OF
12-24
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27


PRESENT
12-25
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27


INVENTION
12-26
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27



12-27
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27



12-28
V
WITHOUT
95
1 × 1015
250
Ge
17
10
1000
27

















COMPARATIVE
12-29
V
WITHOUT
97.5
1 × 1016
250
NONE
10
1000
16


EXAMPLE


















EXAMPLE
12-30
V
WITHOUT
97.5
1 × 1016
250
Ge
17
10
1000
42


OF
12-31
V
WITHOUT
97.5
1 × 1016
250
Ge
17
10
1000
42


PRESENT
12-32
V
WITHOUT
97.5
1 × 1016
250
Ge
17
10
1000
42


INVENTION
12-33
V
WITHOUT
97.5
1 × 1016
250
Ge
17
10
1000
42



12-34
V
WITHOUT
97.5
1 × 1016
250
Ge
17
10
1000
42



12-35
V
WITHOUT
97.5
1 × 1016
250
Ge
I7
10
1000
42

















COMPARATIVE
12-36
V
WITH
95
8 × 1016
250
NONE
10
1000
17


EXAMPLE


















EXAMPLE
12-37
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50


OF
12-38
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50


PRESENT
12-39
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50


INVENTION
12-40
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50



12-41
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50



12-42
V
WITH
95
8 × 1016
250
Ge
17
10
1000
50














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
12-1
13
1100
2
13
13
15
50
13
13


EXAMPLE


EXAMPLE
12-2
16
1000
2
30
11
15
54
30
11


OF
12-3
16
1100
2
30
12
15
54
30
12


PRESENT
12-4
16
1100
5
30
12
15
54
30
12


INVENTION
12-5
16
1100
30
30
12
15
54
30
12



12-6
16
1100
120
30
12
15
54
30
12



12-7
16
1100
360
30
12
15
54
30
12


COMPARATIVE
12-8
13
1100
2
13
13
15
50
13
13


EXAMPLE


EXAMPLE
12-9
10
1000
2
42
4.9
15
54
42
4.9


OF
12-10
10
1100
2
55
2.8
15
54
55
2.8


PRESENT
12-11
10
1100
5
55
2.8
15
54
55
2.8


INVENTION
12-12
10
1100
30
55
2.8
15
54
55
2.8



12-13
10
1100
120
55
2.8
15
54
55
2.8



12-14
10
1100
360
55
2.8
15
54
55
2.8


COMPARATIVE
12-15
14
1100
2
13
13
15
50
13
13


EXAMPLE


EXAMPLE
12-16
3.2
1000
2
61
2.4
15
54
61
2.4


OF
12-17
3.2
1100
2
77
1.3
15
54
77
1.3


PRESENT
12-18
3.2
1100
5
77
1.3
15
54
77
1.3


INVENTION
12-19
3.2
1100
30
77
1.3
15
54
77
1.3



12-20
3.2
1100
120
77
1.3
15
54
77
1.3



12-21
3.2
1100
360
77
1.3
15
54
77
1.3


COMPARATIVE
12-22
13
1150
2
13
13
15
125
13
13


EXAMPLE


EXAMPLE
12-23
17
1000
2
30
10
15
136
30
10


OF
12-24
17
1150
3
32
14
15
136
32
14


PRESENT
12-25
17
1150
7
32
14
15
136
32
14


INVENTION
12-26
17
1150
35
32
14
15
136
32
14



12-27
17
1150
140
32
14
15
136
32
14



12-28
17
1150
420
32
14
15
136
32
14


COMPARATIVE
12-29
14
1150
2
13
13
15
125
13
13


EXAMPLE


EXAMPLE
12-30
4
1000
2
43
4.9
15
136
43
4.9


OF
12-31
4
1150
3
59
1.8
15
136
59
1.8


PRESENT
12-32
4
1150
7
59
1.8
15
136
59
1.8


INVENTION
12-33
4
1150
35
59
1.8
15
136
59
1.6



12-34
4
1150
140
59
1.8
15
136
59
1.8



12-35
4
1150
420
59
1.8
15
136
59
1.8


COMPARATIVE
12-36
13
1150
2
13
13
15
125
13
13


EXAMPLE


EXAMPLE
12-37
3.4
1000
2
58
2.8
15
136
58
2.8


OF
12-38
3.4
1150
3
79
0.8
15
136
79
0.8


PRESENT
12-39
3.4
1150
7
79
0.8
15
136
79
0.8


INVENTION
12-40
3.4
1150
35
79
0.8
15
136
79
0.8



12-41
3.4
1150
140
79
0.8
15
136
79
0.8



12-42
3.4
1150
420
79
0.8
15
136
70
0.8









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the Ge content was 6.4 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 29.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1 k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 29.

















TABLE 29









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
12-1
0
0
13
13
1.60
2.05
0.78
94


EXAMPLE


EXAMPLE
12-2
5
0.1
30
11
1.74
2.05
0.85
64


OF
12-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
12-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
12-5
100
35
30
10
1.74
2.05
0.85
37



12-6
100
73
30
10
1.74
2.05
0.85
43



12-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
12-8
0
0
13
13
1.60
2.05
0.78
93


EXAMPLE


EXAMPLE
12-9
7
0.2
42
4.9
1.82
2.05
0.89
62


OF
12-10
75
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
12-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
12-12
100
42
53
2.7
1.85
2.05
0.90
33



12-13
100
71
53
2.7
1.85
2.05
0.90
38



12-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
12-15
0
0
13
13
1.62
2.05
0.79
95


EXAMPLE


EXAMPLE
12-16
7
0.2
61
2.4
1.91
2.05
0.93
61


OF
12-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
12-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
12-19
100
37
75
1.3
1.95
2.05
0.95
28



12-20
100
72
76
1.4
1.97
2.05
0.96
33



12-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
12-22
0
0
13
13
1.60
2.05
0.78
98


EXAMPLE


EXAMPLE
12-23
10
0.3
30
10
1.74
2.05
0.85
64


OF
12-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
12-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
12-26
100
45
32
9
1.74
2.05
0.85
37



12-27
100
72
32
9
1.74
2.05
0.85
42



12-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
12-29
0
0
13
13
1.60
2.05
0.78
104


EXAMPLE


EXAMPLE
12-30
5
0.1
43
4.9
1.78
2.05
0.87
63


OF
12-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
12-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
12-33
100
38
56
2.2
1.87
2.05
0.91
32



12-34
100
71
56
2.1
1.85
2.05
0.90
38



12-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
12-36
0
0
13
13
1.62
2.05
0.79
98


EXAMPLE


EXAMPLE
12-37
6
0.3
58
2.8
1.89
2.05
0.92
63


OF
12-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
12-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
12-40
100
41
82
0.8
1.97
2.05
0.96
26



12-41
100
76
82
0.8
1.95
2.05
0.95
32



12-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 28, in examples of the present invention (conditions No. 12-2 to No. 12-7, No. 12-9 to No. 12-14, No. 12-16 to No. 12-21, No. 12-23 to No. 12-28, No. 12-30 to No. 12-35, No. 12-37 to No. 12-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 29, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 29, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200 } planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200 } planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1 k maintained a higher property level. Further, it could be confirmed that the core loss W10/1 k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
Thirteenth Experiment
In a thirteenth experiment, correlations between an accumulation degree of {200} planes and an accumulation degree of {222} planes and core loss in 42 kinds of manufacturing conditions (condition No. 13-1 to condition No. 13-42) were studied.
Base metal plates (silicon steel plates) used in the thirteenth experiment contained components of the composition W listed in Table 11 and inevitable impurities, with the balance being Fe. An actually measured value of the A3 point at which the base metal plates used in the thirteenth experiment transformed to a γ single phase was 1010° C. The base metal plates were fabricated in the same manner as that in the fourth experiment. In the condition No. 13-1 to the condition No. 13-42, cold rolling was performed in the same manners as those in the condition No. 4-1 to the condition No. 4-42 respectively.
Next, dislocation density of each of the base metal plates was measured with a transmission electron microscope as in the first experiment. Here, in each of the base metal plates having undergone the blasting, since a texture with high dislocation density was observed in a region 30 μm from the surface, dislocation density in this region was measured. Average values of the obtained dislocation densities are listed in Table 30.
Textures of the base metal plates at room temperature were observed, and it was found that their main phase was an α phase. Further, the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured by the aforesaid method, it was found that, as rolled, the accumulation degree of the {200} planes in the α phase was within a 17% to 24% range and the accumulation degree of the {222} planes in the α phase was within a 17% to 24% range in each of the base metal plates.
Thereafter, W layers as the metal layers were formed on a front surface and a rear surface of each of the base metal plates by a sputtering method, except in the conditions No. 13-1, No. 13-8, No. 13-15, No. 13-22, No. 13-29, and No. 13-36. Thickness of each of the W layers (total thickness on the both surfaces) is listed in Table 30.
Subsequently, heat treatment was applied on the base metal plates on which the metal layers were formed, under various conditions as in the first experiment. Further, three samples were prepared per condition and the accumulation degree of the {200} planes in the α phase and the accumulation degree of the {222} planes in the α phase were measured at three stages of the heat treatment, as in the first experiment. Results of these are listed in Table 30.









TABLE 30









FIRST SAMPLE











BASE METAL PLATE

ACCUMULATION















REDUCTION
DISLOCATION

METAL LAYER
HETING
MEASURED
DEGREE OF



















CONDITION


RATE
DENSITY
THICKNESS

THICKNESS
RATE
TEMPERATURE
{200} PLANE



No.
COMPOSITION
BLASTING
(%)
(m/m3)
(μm)
ELEMENT
(μm)
(° C./s)
(° C.)
(%)





















COMPARATIVE
13-1
W
WITHOUT
95
1 × 1015
100
NONE
5
1010
16


EXAMPLE


















EXAMPLE
13-2
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27


OF
13-3
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27


PRESENT
13-4
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27


INVENTION
13-5
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27



13-6
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27



13-7
W
WITHOUT
95
1 × 1015
100
W
1.2
5
1010
27

















COMPARATIVE
13-8
W
WITHOUT
97.5
1 × 1015
100
NONE
5
1010
15


EXAMPLE


















EXAMPLE
13-9
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41


OF
13-10
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41


PRESENT
13-11
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41


INVENTION
13-12
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41



13-13
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41



13-14
W
WITHOUT
97.5
1 × 1015
100
W
1.2
5
1010
41

















COMPARATIVE
13-15
W
WITH
95
8 × 1016
100
NONE
5
1010
15


EXAMPLE


















EXAMPLE
13-16
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61


OF
13-17
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61


PRESENT
13-18
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61


INVENTION
13-19
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61



13-20
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61



13-21
W
WITH
95
8 × 1016
100
W
1.2
5
1010
61

















COMPARATIVE
13-22
W
WITHOUT
95
1 × 1015
250
NONE
5
1010
15


EXAMPLE


















EXAMPLE
13-23
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26


OF
13-24
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26


PRESENT
13-25
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26


INVENTION
13-26
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26



13-27
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26



13-28
W
WITHOUT
95
1 × 1015
250
W
3
5
1010
26

















COMPARATIVE
13-29
W
WITHOUT
97.5
1 × 1015
250
NONE
5
1010
15


EXAMPLE


















EXAMPLE
13-30
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37


OF
13-31
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37


PRESENT
13-32
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37


INVENTION
13-33
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37



13-34
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37



13-35
W
WITHOUT
97.5
1 × 1015
250
W
3
5
1010
37

















COMPARATIVE
13-36
W
WITH
95
8 × 1016
250
NONE
5
1010
15


EXAMPLE


















EXAMPLE
13-37
W
WITH
95
8 × 1016
250
W
3
5
1010
58


OF
13-38
W
WITH
95
8 × 1016
250
W
3
5
1010
58


PRESENT
13-39
W
WITH
95
8 × 1016
250
W
3
5
1010
58


INVENTION
13-40
W
WITH
95
8 × 1016
250
W
3
5
1010
58



13-41
W
WITH
95
8 × 1016
250
W
3
5
1010
58



13-42
W
WITH
95
8 × 1016
250
W
3
5
1010
58














FIRST SAMPLE
SECOND SAMPLE
THIRD SAMPLE



















ACCUMULATION


ACCUMULATION
ACCUMULATION


ACCUMULATION
ACCUMULATION




DEGREE OF
KEEPING
KEEPING
DEGREE OF
DEGREE OF
COOLING

DEGREE OF
DEGREE OF



CONDITION
{222} PLANE
TEMPERATURE
TIME
{200} PLANE
{222} PLANE
RATE
DISTANCE
{200} PLANE
{222} PLANE



No.
(%)
(° C.)
(s)
(%)
(%)
(° C./s)
(μm)
(%)
(%)





COMPARATIVE
13-1
14
1150
2
13
13
3
50
13
13


EXAMPLE


EXAMPLE
13-2
12
1010
2
30
11
3
54
30
11


OF
13-3
12
1150
2
36
8
3
54
36
8


PRESENT
13-4
12
1150
5
36
8
3
54
36
8


INVENTION
13-5
12
1150
30
36
8
3
54
36
8



13-6
12
1150
120
36
8
3
54
36
8



13-7
12
1150
360
36
8
3
54
36
8


COMPARATIVE
13-8
13
1150
2
13
13
3
50
13
13


EXAMPLE


EXAMPLE
13-9
8
1010
2
43
5.9
3
54
43
5.9


OF
13-10
8
1150
2
57
2.1
3
54
57
2.1


PRESENT
13-11
8
1150
5
57
2.1
3
54
57
2.1


INVENTION
13-12
8
1150
30
57
2.1
3
54
57
2.1



13-13
8
1150
120
57
2.1
3
54
57
2.1



13-14
8
1150
360
57
2.1
3
54
57
2.1


COMPARATIVE
13-15
13
1150
2
13
13
3
50
13
13


EXAMPLE


EXAMPLE
13-16
2.8
1010
2
63
2
3
54
63
2


OF
13-17
2.8
1150
2
83
0.9
3
54
83
0.9


PRESENT
13-18
2.8
1150
5
83
0.9
3
54
83
0.9


INVENTION
13-19
2.8
1150
30
83
0.9
3
54
83
0.9



13-20
2.8
1150
120
83
0.9
3
54
83
0.9



13-21
2.8
1150
360
83
0.9
3
54
83
0.9


COMPARATIVE
13-22
13
1200
2
13
13
3
125
13
13


EXAMPLE


EXAMPLE
13-23
13
1010
2
30
11
3
136
30
11


OF
13-24
13
1200
3
34
10
3
136
34
10


PRESENT
13-25
13
1200
7
34
10
3
136
34
10


INVENTION
13-26
13
1200
35
34
10
3
136
34
10



13-27
13
1200
140
34
10
3
136
34
10



13-28
13
1200
420
34
10
3
136
34
10


COMPARATIVE
13-29
14
1200
2
13
13
3
125
13
13


EXAMPLE


EXAMPLE
13-30
10
1000
2
41
5.3
3
136
41
5.3


OF
13-31
10
1200
3
55
2.5
3
136
55
2.8


PRESENT
13-32
10
1200
7
55
2.8
3
136
55
2.8


INVENTION
13-33
10
1200
35
55
2.8
3
136
55
2.8



13-34
10
1200
140
55
2.8
3
136
55
2.8



13-35
10
1200
420
55
2.8
3
136
55
2.8


COMPARATIVE
13-36
14
1200
2
13
13
3
125
13
13


EXAMPLE


EXAMPLE
13-37
3.2
1010
2
60
2.5
3
136
60
2.5


OF
13-38
3.2
1200
3
82
0.8
3
136
82
0.8


PRESENT
13-39
3.2
1200
7
82
0.8
3
136
82
0.8


INVENTION
13-40
3.2
1200
35
82
0.8
3
136
82
0.8



13-41
3.2
1200
140
82
0.8
3
136
82
0.8



13-42
3.2
1200
420
82
0.8
3
136
82
0.8









Further, an alloying ratio of the metal layer and a ratio of an α single phase region in each of the Fe-based metal plates were measured as in the first experiment. Here, in finding the alloying ratio, a region where the Fe content was 0.5 mass % or less and the content of ferrite former was 99.5 mass % or more was regarded as an alloy layer. Further, a region where the W content was 6.6 mass % or more was regarded as the α single phase region, and a ratio of the α single phase region was found from the aforesaid expression (4). Results of these are listed in Table 31.
Further, as in the first experiment, magnetic flux density B50 and saturation magnetic flux density Bs were measured and a ratio B50/Bs of the magnetic flux density B50 to the saturation magnetic flux density Bs was calculated. Further, core loss W10/1 k (W10/1000) at a 1000 Hz frequency when the magnetic flux density was 1.0 T was measured. Results of these are listed in Table 31.

















TABLE 31









RATIO OF
ACCUMULATION
ACCUMULATION








ALLOYING
α SINGLE
DEGREE OF
DEGREE OF



CONDITION
RATE
PHASE
{200} PLANE
{222} PLANE
B50
Bs
B50/
W10/1k



No.
(%)
(%)
(%)
(%)
(T)
(T)
Bs
(W/kg)

























COMPARATIVE
13-1
0
0
13
13
1.60
2.05
0.78
91


EXAMPLE


EXAMPLE
13-2
7
0.2
30
11
1.74
2.05
0.85
63


OF
13-3
82
1.5
31
10
1.74
2.05
0.85
57


PRESENT
13-4
95
8.2
30
10
1.74
2.05
0.85
44


INVENTION
13-5
100
35
30
10
1.74
2.05
0.85
37



13-6
100
73
30
10
1.74
2.05
0.85
43



13-7
100
87
30
10
1.74
2.05
0.85
58


COMPARATIVE
13-8
0
0
13
13
1.60
2.05
0.78
92


EXAMPLE


EXAMPLE
13-9
10
0.3
43
5.9
1.78
2.05
0.87
61


OF
13-10
64
2.6
53
2.7
1.85
2.05
0.90
57


PRESENT
13-11
94
7.8
53
2.7
1.87
2.05
0.91
42


INVENTION
13-12
100
42
53
2.7
1.85
2.05
0.90
33



13-13
100
71
53
2.7
1.85
2.05
0.90
38



13-14
100
95
53
2.7
1.87
2.05
0.91
53


COMPARATIVE
13-15
0
0
13
13
1.62
2.05
0.79
92


EXAMPLE


EXAMPLE
13-16
5
0.1
63
2
1.91
2.05
0.93
63


OF
13-17
67
1.2
75
1.3
1.95
2.05
0.95
48


PRESENT
13-18
89
5.9
75
1.4
1.93
2.05
0.94
41


INVENTION
13-19
100
37
75
1.3
1.95
2.05
0.95
28



13-20
100
72
76
1.4
1.97
2.05
0.96
33



13-21
100
87
75
1.7
1.95
2.05
0.95
48


COMPARATIVE
13-22
0
0
13
13
1.60
2.05
0.78
99


EXAMPLE


EXAMPLE
13-23
8
0.3
30
11
1.74
2.05
0.85
64


OF
13-24
57
1.2
32
9
1.74
2.05
0.85
56


PRESENT
13-25
87
6.7
32
9
1.74
2.05
0.85
45


INVENTION
13-26
100
45
32
9
1.74
2.05
0.85
37



13-27
100
72
32
9
1.74
2.05
0.85
42



13-28
100
92
32
9
1.74
2.05
0.85
57


COMPARATIVE
13-29
0
0
13
13
1.60
2.05
0.78
101


EXAMPLE


EXAMPLE
13-30
8
0.3
41
5.3
1.78
2.05
0.87
64


OF
13-31
54
1.3
56
2.1
1.87
2.05
0.91
52


PRESENT
13-32
78
6.1
56
2.1
1.85
2.05
0.90
41


INVENTION
13-33
100
38
56
2.2
1.87
2.05
0.91
32



13-34
100
71
56
2.1
1.85
2.05
0.90
38



13-35
100
91
56
2.2
1.87
2.05
0.91
54


COMPARATIVE
13-36
0
0
13
13
1.62
2.05
0.79
102


EXAMPLE


EXAMPLE
13-37
8
0.2
60
2.5
1.89
2.05
0.92
63


OF
13-38
70
2.3
82
0.8
1.95
2.05
0.95
46


PRESENT
13-39
91
7.1
82
0.8
1.95
2.05
0.95
40


INVENTION
13-40
100
41
82
0.8
1.97
2.05
0.96
26



13-41
100
76
82
0.8
1.95
2.05
0.95
32



13-42
100
100
82
0.8
1.97
2.05
0.96
48









As listed in Table 30, in examples of the present invention (conditions No. 13-2 to No. 13-7, No. 13-9 to No. 13-14, No. 13-16 to No. 13-21, No. 13-23 to No. 13-28, No. 13-30 to No. 13-35, No. 13-37 to No. 13-42), the accumulation degree of the {200} planes in the α phase was within the ranges of the present invention at the respective stages of the heat treatment. Further, as listed in Table 31, in the examples of the present invention, the alloying ratio and the ratio of the α single phase region were within the desirable ranges of the present invention. As listed in Table 31, according to the examples of the present invention, the Fe-based metal plates in which the accumulation degree of the {200} planes in the α phase was 30% or more and the accumulation degree of the {222} planes in the α phase was 30% or less were obtained. Further, in the Fe-based metal plates of the examples of the present invention, the ratio B50/Bs was 0.85 or more.
In the examples of the present invention, when the ratio of the α single phase region was 1% or more and the accumulation degree of the {200} planes was 30% or more, not only the magnetic flux density B50 but also the core loss W10/1 k maintained a higher property level. Further, it could be confirmed that the core loss W10/1 k has a still better property level when the ratio of the α single phase region is not less than 5% nor more than 80%.
INDUSTRIAL APPLICABILITY
The present invention is usable in, for example, industries related to magnetic materials such as iron cores.

## Claims

1. A method of manufacturing an Fe-based metal plate comprising:
forming a metal layer containing ferrite former on at least one surface of a base metal plate of an α-γ transforming Fe or Fe alloy;
next heating the base metal plate and the metal layer to an A3 point of the Fe or the Fe alloy so as to diffuse the ferrite former into the base metal plate and form an alloy region of a ferrite phase in which an accumulation degree of {200} planes is 25% or more and an accumulation degree of {222} planes is 40% or less; and
next heating the base metal plate to a temperature equal to or higher than the A3 point of the Fe or the Fe alloy so as to increase the accumulation degree of the {200} planes and decrease the accumulation degree of the {222} planes while maintaining the alloy region of the ferrite phase.

2. The method of manufacturing an Fe-based metal plate according to claim 1, comprising, after the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, cooling the base metal plate to a temperature lower than the A3 point of the Fe or the Fe alloy so as to transform an unalloyed region in the base metal plate from an austenitic phase to a ferrite phase, further increase the accumulation degree of the {200} planes and further decrease the accumulation degree of the {222} planes.

3. The method of manufacturing an Fe-based metal plate according to claim 1, wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the accumulation degree of the {200} planes is increased to 30% or more and the accumulation degree of the {222} planes is decreased to 30% or less.

4. The method of manufacturing an Fe-based metal plate according to claim 1, wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the accumulation degree of the {200} planes is increased to 50% or more and the accumulation degree of the {222} planes is decreased to 15% or less.

5. The method of manufacturing an Fe-based metal plate according to claim 1, wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, the ferrite former contained in the metal layer are all diffused into the base metal plate.

6. The method of manufacturing an Fe-based metal plate according to claim 1, wherein the ferrite former are at least one kind selected from a group consisting of Al, Cr, Ga, Ge, Mo, Sb, Si, Sn, Ti, V, W, and Zn.

7. The method of manufacturing an Fe-based metal plate according to claim 1, wherein, in the increasing the accumulation degree of the {200} planes and the decreasing the accumulation degree of the {222} planes, an area ratio of a ferrite single phase region to the metal plate in a cross section in a thickness direction is made to 1% or more.

8. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a working strain is brought about and in which dislocation density is not less than 1×1015 m/m3 nor more than 1 ×1017 m/m3.

9. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a working strain is brought about by cold rolling in which rolling reduction ratio is not less than 97% nor more than 99.99%.

10. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a working strain is brought about by shot blasting.

11. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a working strain is brought about by cold rolling in which rolling reduction ratio is not less than 50% nor more than 99.99% and shot blasting.

12. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a shear strain of 0.2 or more is brought about by cold rolling.

13. The method of manufacturing an Fe-based metal plate according to claim 1, wherein as the base metal plate, used is one in which a shear strain of 0.1 or more is brought about by cold rolling and a working strain is brought about by shot blasting.

14. The method of manufacturing an Fe-based metal plate according to claim 1, wherein a thickness of the base metal plate is not less than 10 μm nor more than 5 mm.

15. A Fe-based metal plate, containing ferrite former,
wherein, in a surface, an accumulation degree of {200} planes in a ferrite phase is 30% or more and an accumulation degree of {222} planes in the ferrite phase is 30% or less, and the ferrite former is at least one selected from the group consisting of Al, Cr, Ga, Ge, Mo, Sb, Sn, Ti, V, W and Zn,
wherein the Fe-based metal plate is formed by diffusion of the ferrite former from a surface to an inner part of an α-γ transforming Fe or Fe alloy plate, and
wherein a ratio of an α single phase region to the Fe-based metal plate in a thickness direction is not less than 5% and not more than 80%.

16. The Fe-based metal plate according to claim 15, comprising, on the surface, a metal layer containing the ferrite former.

17. The Fe-based metal plate according to claim 15, wherein the accumulation degree of the {200} planes is 50% or more and the accumulation degree of the {222} planes is 15% or less.

18. The Fe-based metal plate according to claim 15, wherein the ferrite former are at least one kind selected from a group consisting of Al, Cr, Ga, Ge, Mo, Sb, Si, Sn, Ti, V, W, and Zn.

19. The Fe-based metal plate according to claim 15, comprising a 1% ferrite single phase region or more in terms of an area ratio in a thicknesswise cross section of the metal plate.