Source: http://www.google.com/patents/US7749614?dq=oakley+D523,461&ei=qiI4T-CjGqXf0QHz_PSUCA
Timestamp: 2016-05-30 17:25:43
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Matched Legal Cases: ['art 1', 'art 4', 'art 1', 'art 4', 'art 4', 'art 4']

Patent US7749614 - Method of brazing a Ti-Al alloy - Google PatentsSearch Images Maps Play YouTube News Gmail Drive More »Sign inPatentsThe invention relates to a method of brazing a Ti—Al alloy. According to the invention, a layer of nickel (2) is disposed between a part (1) which is made from titanium aluminide and a brazing sheet (3), such as to enable: the aforementioned part (1) to be brazed to another metallic material (4) without...http://www.google.com/patents/US7749614?utm_source=gb-gplus-sharePatent US7749614 - Method of brazing a Ti-Al alloyAdvanced Patent SearchPublication numberUS7749614 B2Publication typeGrantApplication numberUS 10/566,052PCT numberPCT/FR2004/001854Publication dateJul 6, 2010Filing dateJul 15, 2004Priority dateJul 25, 2003Fee statusPaidAlso published asEP1648651A2, EP1648651B1, US20070281175, WO2005018867A2, WO2005018867A3Publication number10566052, 566052, PCT/2004/1854, PCT/FR/2004/001854, PCT/FR/2004/01854, PCT/FR/4/001854, PCT/FR/4/01854, PCT/FR2004/001854, PCT/FR2004/01854, PCT/FR2004001854, PCT/FR200401854, PCT/FR4/001854, PCT/FR4/01854, PCT/FR4001854, PCT/FR401854, US 7749614 B2, US 7749614B2, US-B2-7749614, US7749614 B2, US7749614B2InventorsCarine Hoffmann, Marie-Pierre Bacos, Pierre Josso, Serge NaveosOriginal AssigneeOnera (Office National D'etudes Et De Recherches Aerospatiales)Export CitationBiBTeX, EndNote, RefManPatent Citations (12), Non-Patent Citations (3), Referenced by (1), Classifications (29), Legal Events (3) External Links: USPTO, USPTO Assignment, EspacenetMethod of brazing a Ti-Al alloy
US 7749614 B2Abstract
The invention relates to a method of brazing a Ti—Al alloy. According to the invention, a layer of nickel (2) is disposed between a part (1) which is made from titanium aluminide and a brazing sheet (3), such as to enable: the aforementioned part (1) to be brazed to another metallic material (4) without the aluminium diffusing from one to the other; and a stable link with good mechanical strength to be produced. The invention can be used for the assembly of aircraft engine parts which are made from titanium aluminide and nickel-based superalloy.
1. A method of fixing to the surface of a first part comprising a metal material, a second metal material by melting a brazing alloy adapted to the second material, the first material comprising an intermetallic Ti—Al alloy, characterised in that wherein a layer of nickel having a thickness of at least 30 μm is interposed between the first part and the brazing alloy, wherein said method forms a plurality of successive layers over said first part, wherein said plurality of successive layers comprise a first layer comprising phases α2-Ti3Al, τ2-Ti7AlNi and τ3-TiAlNi, and second, third and fourth layers formed respectively of phases τ4-TiAlNi2 and γ′-Ni3Al and of nickel, and a fifth layer comprising the brazing alloy connecting the fourth layer to the second metal material.
7. The method according to claim 1, wherein the layer of nickel has a thickness of at least 40 μm.
9. The method according to claim 1, wherein the first part, the layer of nickel, the brazing alloy and the second material are brought to a temperature higher than the melting temperature of the brazing alloy for at least 10 minutes in a vacuum.
10. The method according to claim 9, wherein the method is carried out under a residual pressure of less than 10−3 Pa.
11. The method according to claim 1, wherein the first layer comprises islets of α2-Ti3Al dispersed in a polyphase matrix comprising τ2-Ti2AlNi and τ3-TiAlNi.
12. The method according to claim 1, wherein the first layer comprises a first sub-layer of α2-Ti3Al and a second polyphase sub-layer comprising τ2-Ti2AlNi and τ3-TiAlNi.
13. The method according to claim 1, wherein the first layer comprises a first sub-layer of α2-Ti3Al, a second sub-layer of τ2-Ti2AlNi and a third sub-layer of τ3-TiAlNi.
14. A composite metal part formed using the method as recited in claim 1, comprising said first part and said plurality of successive layers over said first part, and a second part fixed to said first part via said plurality of successive layers, wherein said plurality of successive layers comprise the first layer comprising phases α2-Ti3Al, τ2-Ti2AlNi and τ3-TiAlNi, and the second, third and fourth layers formed respectively of phases τ4-TiAlNi2 and γ′-Ni3Al and of nickel, and the fifth layer comprising the brazing alloy connecting the fourth layer to the second metal material.
15. The composite metal part according to claim 14, wherein the first layer comprises islets of α2-Ti3Al dispersed in a polyphase matrix comprising τ2-Ti2AlNi and τ3-TiAlNi.
16. The composite metal part according to claim 14, wherein the first layer comprises a first sub-layer of α2-Ti3Al and a second polyphase sub-layer comprising τ2-Ti2AlNi and τ3-TiAlNi.
17. The composite metal part according to claim 14, wherein the first layer comprises a first sub-layer of α2-Ti3Al, a second sub-layer of τ2-Ti2AlNi and a third sub-layer of τ3-TiAlNi.
18. The composite metal part according to claim 14, wherein said second metal material is a nickel-based alloy. Description
The invention relates to a method of fixing to the surface of a first part composed of a first metal material a second metal material, by melting a brazing alloy adapted to the second material, the first material being an intermetallic Ti—Al alloy.
The intermetallic alloy γ-TiAl has the advantage, relative to other titanium-based alloys such as the alloy known as TA6V and to nickel-based alloys, usually used to manufacture aeronautic engine components, of having a low density combined with a mechanical strength comparable to that of steels and of the aforesaid nickel alloys, which permits a considerable reduction in the mass being carried and therefore of specific consumption.
However, intermetallic alloys of the TiAl type cannot be screwed, bolted or riveted without the risk of cracking since they are fragile cold. It is therefore necessary to use another joining technique, in particular adhesion, welding or brazing. Adhered assemblies cannot be used at temperatures higher than 150� C. Welding demands compatibility between the materials to be welded, which does not exist for example between titanium-based alloys and nickel-, cobalt- and/or iron-based alloys. As for brazing of these materials, problems arise due to the fact that titanium forms with nickel, cobalt and iron eutectic alloys with low melting points. It is therefore necessary to resort to diffusion brazing.
U.S. Pat. No. 4,869,421 A and EP 0 904 881 A describe methods of brazing limited to the joining of two parts composed of titanium aluminide. U.S. Pat. No. 5,318,214 A describes a method of brazing applied in particular to the assembly of a part composed of Ti3Al and of a part composed of nickel commercially available under the name Hastelloy X. However, the present inventors have not been able to obtain a join by reproducing the modus operandi described in this document, Ti3Al being replaced by γ-TiAl.
The object of the invention is to form a join by brazing between a first metal material which is some form of Ti—Al alloy and a second metal material which may be in particular an alloy of nickel, cobalt, iron or titanium.
Optional, additional or alternative features of the invention are given below:
The second material takes the form of a second pre-formed part in which the layer of nickel and the brazing alloy are pressed between the first and second parts. The second material takes the form of a covering which is applied over the assembly formed by the first part, the layer of nickel and the brazing alloy. The layer of nickel takes the form of a pre-formed sheet. The layer of nickel takes the form of a covering. The covering of nickel is deposited by electrolytic means. The layer of nickel has a thickness of at least 30 μm and preferably at least 40 μm. The second material is a nickel-based alloy. The assembly to be processed is raised to a temperature higher than the melting point of the brazing alloy for at least ten minutes in a vacuum. The operation is carried out under a residual pressure lower than 10−3 Pa. The further object of the invention is a composite metal part such as can be obtained by the method as defined above, comprising a substrate and an intermetallic Ti-AL alloy, covered with a large number of successive coats, notably a first coat containing the phases α2-Ti3AL, τ2-Ti2ALNi and τ3-TiALNi, second, third and fourth layers formed respectively of the phases τ4-TiALNi2 and γ′-Ni3Al and of nickel, and a fifth layer of brazing alloy joining the fourth layer to another metal material.
The part according to the invention may comprise at least some of the following features:
the first layer contains islets of α2-Ti3Al dispersed in a polyphase matrix comprising α2-Ti2AlNi and τ3-TiAlNi. The first layer comprises a first sub-layer of α2-Ti3Al and a second polyphase sub-layer comprising α2-Ti2AlNi and τ3-TiAlNi. The first layer comprises a first sub-layer of α2-Ti3Al, a second sub-layer of τ2-Ti2AlNi and a third sub-layer of τ3-TiAlNi. The other metal material is a nickel-based alloy. The features and advantages of the invention are explained in more detail in the description below with reference to the attached drawings.
The two parts to be assembled shown in FIG. 1 are a part 1 composed of titanium aluminide and a part 4 composed of nickel-based alloy. According to the invention, the part 1 is deposited on a sheet of nickel 2 whose thickness is preferably at least 40 μm. The assembly is then deposited on a strip 3 of a conventional brazing alloy which may be for example one of the alloys known as TiCuNi 70, TiNi 67 and MBF 1006, or nickel boride BNi3 or silver-copper eutectic alloy, and the whole is deposited on the part 4. The stack obtained is placed in a furnace in a vacuum whose residual pressure is lower than 10−3 Pa, and is heated to a temperature higher than the melting point of the brazing alloy 3. To improve the quality of the brazed joint, the stack may be subjected to slight compression. A duration of the temperature level of about one hour makes it possible to obtain solidification of the brazing alloy by diffusion of its constituents into the other layers (isothermic solidification), leading to the structure shown in FIG. 2.
In FIG. 2, an interdiffusion layer 5 adjacent to the titanium aluminide substrate 1 is formed of islets of α2-Ti3Al 5-1 dispersed in a polyphase matrix 5-2 containing the phases τ2-Ti2AlNi and τ3-TiAlNi. The layer 5 is followed by a continuous layer 6 of the phase τ4-TiAlNi2 and then a continuous layer 7 of γ′-Ni3Al, itself being adjacent to the layer 2 of pure nickel. Between the latter and the part 4 is interposed a layer 8 resulting from the diffusion of the elements of the brazing alloy into the layer 2 and into the part 4.
This example shows the brazing of a part composed of the alloy γ-TiAl and of a part composed of a nickel alloy sold under the name Nimonic 75. To this end, a sheet of nickel of 60 μm thickness is inserted between a brazing alloy of TiCuNi and the part composed of titanium aluminide, the part composed of nickel alloy being directly in contact with the brazing alloy. The assembly is brought under a pressure of 5 kPa to a temperature of 1050� C. in a vacuum better than 10−3 Pa for two hours. At the TiAl/nickel interface, aluminium migrates from the TiAl to the nickel. Thus four layers are formed containing respectively 35%, 39%, 26% and 13% aluminium atoms. The result is a stable assembly free of cracks.
The sheet of nickel prevents the diffusion of aluminium towards the nickel alloy. The brazing alloy has few precipitates distributed in a non-uniform manner. It is formed of plural phases of different interlocking compositions, notably:
a dark grey phase of an atomic composition Ti 54%, Ni 30%, Cr 10%; a light grey phase and a white phase of respective compositions Ni 45.5%, Ti 38% and Ni 62.5%, Ti 26%, corresponding to the phases TiNi and Ti3Ni of the binary Ti—Ni diagram; and a black phase of composition Ti 87%, Ni 9% (β-Ti). Nickel diffuses from the nickel alloy to the brazing alloy as is demonstrated by the present of precipitates of pure chromium at the place of the initial interface. A phase is also present containing nickel, titanium and chromium (αTi+η-Ni3Ti+γ-NiCr), titanium being capable of coming either from the brazing alloy or from the TiAl, probably from the latter, the fusion zone of the brazing alloy being low in titanium. The brazing alloy brings about the following reactions:
On the side of the titanium aluminide
3TiAl→Ti3Al+2Al
And on the side of the nickel alloy
6Ni+2Al→2Ni3Al
Or the overall reaction
3TiAl+6Ni→Ti3Al+2Ni3Al.
The concentration gradient of titanium which results is demonstrated by the presence of different compounds defined along the path of diffusion, forming the layers 5 to 7 described above in relation to FIG. 2. Thus a thermodynamic balance is present.
Brazed samples have been aged in argon at 800� C. for 150 hours. The structure of the interface between the nickel/brazing alloy remains unchanged. The distance between the alloy and the sheet of nickel decreases from 120 to 75 μm. The diffusion front of the nickel has therefore advanced. The TiAl/nickel interface has not moved, which shows that the sheet of nickel effectively stops the diffusion of aluminium. The uniformity of the brazing alloy is increased by ageing.
No development of the interface between the nickel alloy and the brazing alloy was found when the duration of ageing was increased to 300 hours. The phase Ti—Ni—Cr, already reduced after 150 hours, is then totally re-dissolved in its matrix. There only remain in the Ni3Ti matrix precipitates of chromium.
Mechanical shearing tests have given strength values τ=221.4�7.5 MPa. A metallographic examination after testing shows that the brazed parts are not separated, but that the cracking produced has been deflected, so that it would render unusable an industrial object obtained from this example. This indicates that the layer of nickel acts as a damper which absorbs the thermomechanical stresses (e.g. dilation) or purely mechanical stresses (shearing, fatigue).
The method is the same as in Example 1, replacing the sheet of nickel with an electrolytic deposition of nickel. To this end, the titanium aluminide is subjected to pre-treatment by sandblasting followed by activation in an aqueous solution containing 40% nitric acid and 3.6% of hydrofluoric acid by mass. The deposition is carried out in a solution of nickel sulphamate dead bath ready for use sold by the firm Frappaz-Imaza, at a temperature of 45� C. and at a current density of 3 A/dm2. As preliminary tests have shown that the thickness of the nickel must be at least 30 μm, a value of 40 μm was selected.
By following the method of Example 2, a layer of nickel is deposited having a thickness of about 50 μm on to a part composed of a nickel alloy commercially available under the name Hastelloy X. As a brazing alloy, silver-copper eutectic alloy is used, whose melting point is 790� C. The melting points of the different eutectic alloys which may form with titanium are the following: Ag—Ti 960� C., non-eutectic melting, Cu—Ti 885� C. and 960� C., NiTi 942� C. The sheet of brazing alloy is interposed between the nickel covering and a part composed of γ-TiAl and the whole is brought to a temperature of 820� C., 65� C. lower than the lowest of the above melting points, under mechanical pressure of 5 kPa and a vacuum better than 10−3 Pa for one hour. After this treatment, the metallographic examination shows a perfect join having the same layers containing Ti and Al as before, and in contact with the nickel alloy a layer of AgCu followed by a layer of NiCuAg. If the Ag—Cu brazing alloy is replaced by pure silver, with a contact pressure of about 1 MPa, the adjacent layer to the nickel alloy and of silver, followed by a layer of γ-Ni.
This example relates to the brazing of γ-TiAl with a nickel alloy commercially available under the name N 18, and aims to resolve the difficult problem, taking into account the cold fragility of γ-TiAl-type alloys, of fixing of the mobile vanes of aeronautical turbine compressors to discs composed of N 18 alloy, the latter being composed of a nickel-based alloy containing by mass 15.5% cobalt, 11.5% chromium, 6.5% molybdenum, 4.3% aluminium, 4.3% titanium and traces of zirconium, carbon, boron and hafnium.
The method is as in Example 2, replacing the alloy Nimonic 75 with the alloy N 18 and using as a brazing alloy TiNi 67. After this treatment, the TiAl/Ni interface is similar to that obtained in the preceding examples. The diffusion zone between the nickel alloy and the brazing alloy is composed of precipitates of titanium and chromium-molybdenum phase. The assembly can operate at temperatures of 800� C. for more than 300 hours.
This example shows the formation on a part composed of γ-TiAl of a protection barrier against oxidation and hot corrosion.
A coating of nickel is formed on a sample of γ-TiAl as is described in Example 2, and this coating is covered with a sheet of brazing alloy TiNi 67, then with a sheet of a thickness of 0.1 mm obtained by sintering from a MCrAlY-type alloy available under the name AMDRY 997, which is a nickel-based alloy containing by mass 23% cobalt, 20% chromium, 8.5% aluminium, 4% tantalum and 0.6% yttrium. Heat treatment under vacuum is carried out as is described in Example 2. After this treatment, metallographic examination shows a perfect join having the sequence of layers already described from the substrate TiAl to the nickel sheet. The MCrAlY sheet is strongly adhesive and can thus ensure protection against oxidation and hot corrosion, in particular in the presence of condensed or non-condensed phases containing chlorine.
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