Abstract:
The object of this invention is to propose the variable capacity turbine, in which the adjustment works can be simplified to decrease man-hours, as well as assembly and adjustment costs. The structure can also be simplified to decrease part category numbers and the number of the parts itself, thus decreasing part costs and furthermore enabling the nozzle vane setup of the adjustable nozzle mechanism to a comparatively high degree of accuracy without being influenced by the degree of dimensional accuracy of the component parts, such as the nozzle vane and the link assembly. To assemble the adjustable nozzle mechanism used in such variable capacity turbine, it needs the steps of providing a plurality of joint members (lever plates) which are the same in number as the nozzle shafts, and connect a plurality of nozzle vanes and the nozzle driving member; fitting and fixing each nozzle shaft to one end of each lever plate after setting the predetermined positional relationship between the wing angle of the nozzle vanes and the predetermined fitting direction of the fixed section of the lever plate; and engaging another end of each lever plate with the nozzle driving member.

Description:
BACKGROUND OF THE INVENTION  
         [0001]    1. Field of Invention  
           [0002]    This invention, as used in a supercharger (an exhaust gas turbocharger) of internal combustion engines or the so forth, relates to the adjustable nozzle mechanism for variable capacity turbines and its production method, with regard to the radial flow turbine configured to make the actuating gas flow from the spiral scroll formed in the turbine casing to the turbine rotor in the radial axis through the multiple nozzle vanes having wings of variable angle.  
           [0003]    2. Description of the Related Art  
           [0004]    In order to make a good match with regard to the internal combustion engine, between the outflow exhaust gas volume from the engine and the actuating gas flow volume which should be determined for the optimum operation condition of the supercharger, variable capacity superchargers, equipped with the variable capacity turbine capable of changing the exhaust gas volume to be sent from the spiral scroll to the turbine rotor in accordance with the operation condition of the engine, have been in widespread use in recent years.  
           [0005]    A supercharger with such a variable capacity turbine is equipped with the adjustable nozzle mechanism in order to change the wing angle of the nozzle vane by rotating the nozzle vane with the link assembly so that it is capable of being driven for rotations around said turbine rotor shaft by the actuator through the actuator rod and the driving lever.  
           [0006]    For the method to achieve assembling and adjustment of such variable nozzle mechanism, an invention of Japanese patent number 3,085,210 has been proposed.  
           [0007]    In the concerned invention, a jig should be placed in the inner radius of the nozzle vane to perform the setup for total shutdown of the nozzle vane and the link assembly to be driven for rotations around the turbine rotor shaft. The jig therein can be put in contact with the rear edge of the nozzle vane, wherein the stopper pin is mounted after the nozzle vane and the lever plates are welded together upon putting the nozzle vane in contact with the jig in the state that the stopper pin, that is to be fitted into the long slots given at the multiple positions along the circumferential direction of the link plate, is made non-functional or non-existing, and upon fitting the matching pin into the phase matching hole to finalize the entire link assembly in the perfectly total shutdown phase.  
           [0008]    However, problems, such as the following, are concerned with the invention of Japanese patent number 3,085,210. Two different processes are required one of which is to put the jig in contact with the nozzle vane in the nozzle vane-free state wherein the stopper pin to be fitted into the long slots of the link plate is non-functional, and the other is to mount the stopper pin after welding the nozzle vane and the lever plate in the perfectly total shutdown phase of the entire link assembly with the matching pin fitted into the phase-matching hole in the state. This in turn requires more assembling jigs, making the adjustable nozzle mechanism assembly and the related adjustment works troublesome, with additional man-hours resulting in cost increase.  
           [0009]    In addition, on the basis of the conventional art in which the structure becomes complex due to the link position determining pin included therein with the stopper pin fitted into the long slot at the multiple positions in the circumferential direction of the link plate, the number of the part category and the number of the parts themselves will therefore increase considerably. As a result, the device costs will increase accordingly.  
           [0010]    Furthermore, as the setup of the total adjustable nozzle mechanism should be carried out by means of fitting the stopper pin into the long slot at multiple positions in the circumferential direction of the link plate and by means of making a match of the relative angle of the contact of the jig at the nozzle vane rear edge against the lever plate, the setup of the total shutdown may vary to cause a setup error. The total shutdown position of the adjustable nozzle mechanism must be determined primarily by the dimensional accuracy of the component parts, which may make it difficult to obtain the proper setup accuracy.  
         SUMMARY OF THE INVENTION  
         [0011]    In consideration of the problems with the conventional art mentioned above, the object of this invention is to propose the method to realize assembly and adjustment, and the related assembly and adjustment facilities for the variable capacity turbine, requiring neither adjustment of the total shutdown position in the nozzle assembly nor the jigs for assembly and adjustment thereof, by which the adjustment works can be simplified to decrease man-hours, as well as assembly and adjustment costs. The structure can also be simplified to decrease part category numbers and the number of the parts itself, thus decreasing part costs and furthermore enabling the nozzle vane setup of the adjustable nozzle mechanism to a comparatively high degree of accuracy without being influenced by the degree of dimensional accuracy of the component parts, such as the nozzle vane and the link assembly.  
           [0012]    In order to solve the concerned problems, the variable capacity turbine for applying this invention comprises; a number of nozzle vanes, which are arranged along the circumference of the turbine and provided on the nozzle shafts which are supported on the turbine casing in such a way that the nozzle vanes can rotate, and which vary the vane angle; a nozzle driving member driving the nozzle vanes, and enabled to rotate around the turbine shafts by the actuator; and a turbine rotor set free for rotation inside the inner radius of the nozzle vanes. The variable capacity turbine is driven for rotation of the turbine rotor by flowing the actuating gas from the scroll in the turbine casing toward the inner radial direction through the nozzle vanes to the turbine rotor.  
           [0013]    In the event of manufacturing the adjustable nozzle mechanism used in such variable capacity turbine, it is distinguished by the manufacturing method according to this invention which comprises the steps of: providing a plurality of joint members (lever plates) which are the same in number as the nozzle shafts, and connect the plurality of nozzle vanes and the nozzle driving member (link plate); fitting and fixing each nozzle shaft to one end of each lever plate after setting the predetermined positional relationship between the wing angle of the nozzle vanes and the fitting direction of the fixing section of the lever plate; and engaging another end of each lever plate with the nozzle driving member (link plate).  
           [0014]    For the concrete fixing method of the nozzle shaft to joint member (lever plate), the method comprises the steps of: forming a coupling hole in each joint member (lever plate), then forming a flat or curved surface on one sidewall of each coupling hole; forming a coupling shaft provided with a fitting surface on the end of the nozzle shaft for nozzle vane, the fitting surface corresponding to the shape of the coupling hole of the joint member (lever plate) for creating a stopper; fitting the coupling shaft into the coupling hole without causing plasticity deformation at the coupling shaft or coupling hole, and engaging the stopper surface of the shaft with the stopper surface on the coupling hole so that the joint member (lever plate) and the nozzle shaft cannot rotate relatively by the stopper, and finally processing for anti-decoupling to prevent the nozzle shaft from squeezing out of the side surface of the joint members by using the chamfered portion having a larger diameter (chamfered portion) at the edge portion of the nozzle shaft.  
           [0015]    The anti-decoupling is preferably processed by punching the shaft edge of the coupling shaft by using the chamfered portion at the edge after engaging the coupling hole of the joint member with the coupling shaft of the nozzle shaft. The anti-decoupling process thereof at the edge can be substituted by a light welding or the like.  
           [0016]    This invention further features that the concrete engaging method of the joint members (lever plate) with the nozzle driving member (link plate) is to fit the slots with the fitting pins equal in number to the joint members. The fitting pins protrude along the circumferential direction on the nozzle driving member. The slots are opened in a nearly radial axis on the other edge of each of the joint members to engage with the fitting pins of the nozzle driving member.  
           [0017]    The variable capacity turbine for applying this invention comprises; a number of nozzle vanes, which are arranged along the circumference of the turbine and provided on the nozzle shafts which are supported on the turbine casing in such a way that the nozzle vanes can rotate, and which vary the vane angle; a nozzle driving member driving the nozzle vanes, and enabled to rotate around the turbine shafts by the actuator; and a turbine rotor set free for rotation inside the inner radius of the nozzle vanes. The variable capacity turbine is driven for rotation of the turbine rotor by flowing the actuating gas from the scroll in the turbine casing towards the inner radial direction through the nozzle vanes to the turbine rotor.  
           [0018]    The adjustable nozzle mechanism used in such variable capacity turbine is distinguished by the configuration, comprising: a plurality of lever plates which are provided between the nozzle mount and the link plate, one end of each lever plate being fitted and fixed to each nozzle shaft after setting the predetermined positional relationship between the wing angle of the nozzle vanes and the fitting direction of the fixing section of the lever plate, and the lever plate being provided with a slot which is opened in a nearly radial axis on the other edge; and the same number of fitting pins protruding along the circumferential direction and toward the lever plate side on the nozzle driving member, the fitting pins being engaged with the slots of the lever plates.  
           [0019]    In accordance with this invention, adjustment of the adjustable nozzle mechanism, that is, the position setup of the wing angle of the nozzle vane and the nozzle driving member, can be made in such extremely simple processes. In this process, the coupling hole provided at one edge of the lever plate and the coupling shaft at the end of the nozzle shaft are fitted after being set up geometrically so that the wing angle and the rotating angle of the link plate composing the nozzle driving member may be in the predetermined relation. The edge of the nozzle shaft is then punched into one of the chamfered portion of the edge portion in order to be fixed on the lever plate. Then the lever plate and the link plate can be engaged to each other by engaging the pins with the slots provided at the end of the lever plate.  
           [0020]    With these simplified processes, adjustment of the adjustable nozzle mechanism during the nozzle assembly procedure is no longer required and therefore the assembling man-hours are decreased, particular assembling facilities such as the jigs are not needed, and as a result, assembling costs are decreased. The jigs are still required with the invention of the Japanese patent number 3,085,210 in such a way that the adjustment should be made for the total shutdown position during nozzle assembly procedure by using multiple long slots of the link plate, stopper pin and jigs.  
           [0021]    Furthermore, as the adjustable nozzle mechanism according to this invention is configured in the manner that the one edge side of the joint members (lever plate) and the nozzle shaft are fixed upon the set geometrical relations between thereto and the nozzle driving member (link plate) are joined to the other edge side of each joint member, the structure is simplified comparatively with the conventional art and the number of part category and parts itself are considerably decreased. Part costs are decreased accordingly.  
           [0022]    Furthermore, with this invention, configured such that the nozzle driving member is joined to the other edge of each joint member after these have been fitted on the condition that the wing angle of the nozzle vane and the rotating angle of the nozzle driving member (link plate) had been set previously in the geometrical relation as required, and that adjustment of the adjustable nozzle mechanism, that is, the position setup of the wing angle of the nozzle vane and the nozzle driving member is available neither with a setting error that would arise in the conventional art from the variable setup for the total shutdown caused by the adjustment for the total shutdown position during nozzle assembling procedure using the multiple long slots, the stopper pin and jig, nor the total shutdown position of the adjustable nozzle mechanism should be determined primarily by the component parts, the setup herein of the adjustable nozzle mechanism is available to a high degree of accuracy without fear of influence by the dimensional accuracy of the nozzle assembly and the link assembly, as well as the enabling of the various requirement settings of the adjustable nozzle mechanism.  
           [0023]    Still furthermore, with this invention, configured such that the lever plates equal in number to the nozzle vanes are placed between the nozzle mount and the link plate in the turbine shaft axis, that the one edge of the lever plate is fixed on the nozzle shaft of the nozzle vane, that the fitting pin protruding toward the lever plate side in the link plate is fitted into the slots on the other edge of the lever plate, that the stopper between the lever plate and the edge of the nozzle shaft is processed with the use of the chamfered portion in order to prevent the stopper portion from squeezing out of the side face of the lever plate, It becomes possible to assemble the link plate and lever plate with a minimum distance, therefore, the distant between the link plate and the nozzle mount over the lever plate sandwiched thereby becomes shorter, and the length in the shaft axis of the adjustable nozzle mechanism is, as a result, shortened.  
           [0024]    Still furthermore, the punched portion avoids protrusion from the link plate side, and erroneous operation of the adjustable nozzle mechanism by the friction and interference between the link plate and the punched portion is also avoided. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0025]    [0025]FIG. 1 shows the cross-sectional view along the rotor shaft of the adjustable nozzle mechanism for the supercharger with the variable capacity turbine in connection with this invention, corresponding to the Z section in FIG. 8.  
         [0026]    [0026]FIG. 2 shows the cross-sectional view corresponding to the Y section in FIG. 1 for the coupling section of the nozzle shaft and the lever plate.  
         [0027]    [0027]FIG. 3 shows the C-arrowed view in FIG. 2.  
         [0028]    [0028]FIG. 4 shows the diagonal view of the coupling section of the nozzle vane and the lever plate.  
         [0029]    [0029]FIG. 5 shows the detailed cross-sectional view of the X section in FIG. 1.  
         [0030]    [0030]FIG. 6 shows the A-arrowed view in FIG. 1.  
         [0031]    [0031]FIG. 7 shows the B-arrowed view in FIG. 1.  
         [0032]    [0032]FIG. 8 shows the key cross-sectional view along the rotor shaft of the supercharger with the variable capacity turbine to which this invention is applicable. 
     
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0033]    In the following section we shall give a detailed explanation of the invention with reference to the drawings. Insofar as the circuit components, control state, relative position of circuit components, or other features of the constitutive circuitry disclosed in this embodiment are not exhaustively delineated, they are not intended to limit the scope of the invention, but serve merely as examples to clarify the explanation.  
         [0034]    [0034]FIG. 1 shows the cross-sectional view along the rotor shaft of the adjustable nozzle mechanism for the supercharger with the variable capacity turbine in connection with this invention, corresponding to the Z section in FIG. 8. FIG. 2 shows the cross-sectional view corresponding to the Y section in FIG. 1 for the coupling section of the nozzle shaft and the lever plate. FIG. 3 shows the C-arrowed view in FIG. 2. FIG. 4 shows the diagonal view of the coupling section of the nozzle vane and the lever plate. FIG. 5 shows the detailed cross-sectional view of the X section in FIG. 1. FIG. 6 shows the A-arrowed view in FIG. 1. FIG. 7 shows the B-arrowed view in FIG. 1. FIG. 8 shows the key cross-sectional view along the rotor shaft of the supercharger with the variable capacity turbine to which this invention is applicable.  
         [0035]    In FIG. 8 showing the entire structure of the supercharger with variable capacity turbine to which this invention is applicable,  30  is a turbine casing, and  38  is a scroll formed in spiral around the circumference section in the turbine casing  30 .  34  is a turbine wheel,  35  is a compressor wheel,  033  is a rotor shaft to join the turbine wheel  34  to the compressor wheel  35 , both of which compose the turbine rotor  33 .  
         [0036]    [0036] 08  is a exhaust gas outlet sending out the exhaust gas having done the expansion work in the turbine rotor  33 .  31  is a compressor casing,  36  is the bearing housing to join the compressor casing  31  and the turbine casing  30 .  37  is the bearing supporting the turbine rotor  33  as mounted on the bearing housing  36 .  
         [0037]    [0037] 2  is a nozzle vane, as placed equidistant in multiple along the circumferential direction of the turbine on the inner radius of the scroll  38 , and the nozzle shaft  02  formed into thereof is supported for the rotary motion by the nozzle mount  4  fixed on the turbine casing  30 , the wing angle of which is changeable.  
         [0038]    [0038] 40  is the actuator rod, that is, the output end of the actuator  040  to drive the nozzle vane  2 , and the reciprocating motion of the actuator rod  40  is converted through the known link mechanism including the driving lever  41  into the rotating motion to be transferred to the link plate  3  of the adjustable nozzle mechanism  100  described later.  
         [0039]    In the supercharger with the variable capacity turbine in such composition, the exhaust gas from the internal combustion engine (not shown in figures here) flows into the scroll  38  and goes around along the spiral of the scroll  38  further to the nozzle vane  2 . The exhaust gas runs through the wings of the nozzle vane  2  to flow into the turbine rotor wheel  34  from the outer radius side thereof, and, after flowing in radial axis towards the shaft axis to perform the expansion work, flows in the shaft axis to the outside from the exhaust outlet  08 .  
         [0040]    [0040] 100  is the adjustable nozzle mechanism rotating the nozzle vane  2  in order to change the wing angle thereof by use of the link plate  3  driven in rotation around the rotating shaft  8  of the turbine rotor  33  through the link mechanism, including the actuator rod  40  and the driving lever  41  from the actuator  040 .  
         [0041]    This invention relates to the production method of such an adjustable nozzle mechanism and the structure of the adjustable nozzle mechanism  100  produced by such a method.  
         [0042]    In FIGS.  1  to  7  showing the preferred embodiments of this invention,  3  is a link plate formed in the disk, being joined to the actuator rod  40  for rotating motion around the rotating shaft  8  through the link mechanism including the driving lever  41  as described above.  
         [0043]    [0043] 4  is the ring-shaped nozzle mount fixed on the turbine casing  30 .  7  is the nozzle support, four of which (or any plural number of which) are placed along the circumferential direction between the nozzle mount  4  and the nozzle plate  12  as shown in FIG. 7 to fix the nozzle mount  4  and the nozzle plate  12 . The coupling section on the nozzle plate  12  side of the nozzle support  7  is processed for a detent function by fitting the parallel shaft section  7   a  formed at the shaft edge section of the nozzle support  7  into the parallel hole section formed in the hole  12   a  of the nozzle plate  12 , as shown in FIG. 5, to punch and fix the shaft edge of the nozzle support  7  on the nozzle plate  12  through the washer  012 .  
         [0044]    On the other hand, the nozzle vane  2  is placed at the inner radius section of the nozzle support  7  between the nozzle mount  4  and the nozzle plate  12 , and the nozzle shaft  02  fixed thereon (or formed into the nozzle vane  2 ) is supported for rotating motion.  
         [0045]    [0045] 1  is the lever plate to compose the joint members joining the link plate  3  to the nozzle shaft  02  on each nozzle vane  2  side, being placed equal in number to the nozzle vane  2 , where one edge side thereof is fixed on the nozzle shaft  02  and the other edge side is joined to the link plate  3 , as described later.  
         [0046]    As shown in FIGS. 2 and 4, the coupling hole  1   b  is provided through to the nozzle shaft  02  on one edge side of the lever plate  1 . The coupling hole  1   b  forms an oval shape having stopper surface in hole  1   d  in parallel therein onto each of the two opposite surfaces.  
         [0047]    On the other hand, the coupling shaft  02   a  is provided to be fitted to the coupling hole  1   b  at the shaft edge of the nozzle shaft  02  of the nozzle vane  2 . The coupling shaft  02   a  forms in the same oval shape as the coupling hole  1   b  to be fitted thereto, and, as the stopper surface on shaft  02   b  thereon in parallel to each other are attached to the stopper surface in hole  1   d , the lever plate  1  and the nozzle vane  2  are fitted firmly so as to disable relative rotation.  
         [0048]    After the coupling shaft  02   a  is fitted to the coupling hole  1   b,  the edge portion of the coupling shaft  02   a  is processed by punching (at  2   a ) to prevent from disconnection, as shown in the FIG. 2.  
         [0049]    As shown in FIGS. 3, 4 and  6 , on the other edge side of the each lever plate  1 , slot  1   c  is formed in the radial axis and the slot  1   c  is fitted with the fitting pin section  3   a  having the fitting pin  3  protruding towards the lever plate in the same quantity as the lever plate  1  protruding towards the lever plate  1  on the side surface of the lever plate  1  of the link plate  3 .  
         [0050]    And the lever plate  1  is placed between the nozzle mount  4  and the link plate  3  in the turbine shaft axis, and, as described above, the one edge side, that is the inner radius side, is fixed on the nozzle shaft  02  and the other edge side, that is the outer radius side, is fixed on the fitting pin section  3   a  of the link plate  3 .  
         [0051]    In order to control the capacity of the variable capacity turbine equipped with the adjustable nozzle mechanism  100  in such a composition, the wing angle of the nozzle vane  2  should be set up by means of wing angle control (not shown in figures here) to the required flow volume of the exhaust gas flowing through the nozzle vane  2  against the actuator  040 . The reciprocating displacement of the actuator  040  corresponding to such wing angle is converted into rotating motion by the link mechanism including the actuator rod  40  and the driving lever  41 , and transferred to the link plate  3  to drive the link plate  3  for rotation.  
         [0052]    By the rotation of the link plate  3 , each lever plate  1 , joined by the fitting of fitting pin section  3   a  and slot section  1   c  to the link plate  3 , is shaken around the shaft of the nozzle shaft  02  by the shift of the fitting pin section  3   a  in the circumferential direction of the rotation by the link plate  3 , then the nozzle shaft  02  is rotated by the rotation of lever plate  1 , and the nozzle vane  2  rotates in order to change itself to the wing angle set up by the actuator  040 .  
         [0053]    When fitting the coupling shaft section  02   a  of the nozzle vane  2  to the coupling hole  1   b  of the lever plate  1  in such an embodiment, the abovementioned stopper surface in hole id of the coupling hole  1   b  and the stopper surface on shaft  02   b  of the coupling shaft section  02   a  are attached to be fitted after the wing angle of the nozzle vane  2  and the rotating angle of the link plate  3  are set geometrically in the required relation, and then processed for disconnection prevention by punching the edge of the coupling shaft section  02   a.    
         [0054]    In such a punching process, the outside of the coupling hole  1   b  of the lever plate  1  is made as chamfered beforehand as shown in FIG. 2 ( 01   b  showing the chamfered portio), and after the coupling hole  1   b  of the lever plate  1  and the coupling shaft section  02   a  of the nozzle shaft  02  are fitted, the coupling shaft section  02   a  is punched along the chamfered portion  01   b . At this time, a punching process is taken in use of the chamfered portion  01   b  so that the punched part  2   a  at the shaft edge of the coupling shaft  02   a  may not squeeze out towards the inside from the side surface  1   a  of the lever plate  1 .  
         [0055]    By such a punching process, the punched part  2   a  of the nozzle shaft  02  avoids protrusion from the link plate  3 , erroneous operation of the adjustable nozzle mechanism  100  by friction between the protruding part and the link plate  3  is prevented, the distance in the shaft axis of the lever plate  1  from the link plate  3  is made shortest, and therefore the length in the shaft axis of the adjustable nozzle mechanism is shortened.  
         [0056]    In accordance with such an embodiment, the coupling hole  1   b  (stopper surface in hole  1   d ), formed at one edge side of the lever plate  1 , and the coupling shaft section  02   a  (stopper surface on shaft  02   b ) of the nozzle shaft  02  are fitted upon setting beforehand the wing angle of the nozzle vane  2  and the rotating angle of the link plate  3  geometrically in the required relation, and adjustment of the adjustable nozzle mechanism  100 , that is, the position setup between the wing angle of the nozzle vane  2   a  and the link plate  3 , is carried out by an extremely easy method such that, after the edge of the nozzle shaft  02  (coupling shaft section  02   a ) is punched at the chamfered portion  01   b  to be fixed on the lever plate  1 , the fitting pin section  3   a  of the link plate  3  is fitted to the slot  1   c  formed at the other side of the each lever plate  1 .  
         [0057]    This easy method does not require adjustment of the adjustable nozzle mechanism  100  during the nozzle assembly procedure, in which the total shutdown position should be adjusted during the nozzle assembly procedure by using the multiple long slots of the link plate, the stopper pin and the jigs, as had been required with the invention of Japanese patent number 3,085,210. Therefore, the assembling man-hours are decreased, particular assembling facilities such as the jigs are not needed, and as the result the assembling costs are decreased.  
         [0058]    In addition, the adjustable nozzle mechanism  100  is so composed to join the link plate  3  to the other edge side of the each lever plate  1  after setting and fixing the geometrical relation between one edge side of the lever plate  1  and the nozzle shaft  02  as described above, therefore the structure is simplified comparatively with the technology, the number of part categories and the parts themselves are considerably decreased, and part costs are decreased accordingly.  
         [0059]    Further, in accordance with such an embodiment, adjustment of the adjustable nozzle mechanism  100 , that is the position setup between the wing angle of the nozzle vane  2  and the link plate  3  can be carried out by means of joining the link plate  3  to the other edge of the each lever plate  1  after fitting and fixing upon setting up beforehand the one edge of the lever plate  1  and the nozzle shaft  02  geometrically so that the wing angle of the nozzle vane  2  and the rotating angle of the link plate  3  are in the required relation, variations or error may not occur in the setup for the total shutdown, which occurred due to the adjustment to be done with the conventional art for the total shutdown position during nozzle assembling procedure using the multiple long slots of the link plate, stopper pin and jigs. However, with this invention, the total shutdown position of the adjustable nozzle mechanism is not determined primarily by the dimensional accuracy of the component parts, the setup of the adjustable nozzle mechanism  100  is available while securing a high degree of accuracy without being influenced by the dimensional accuracy of the nozzle assembly or the link assembly, and as a result, the adjustable nozzle mechanism  100  can be set up to the various requirements.  
         [0060]    Also, in accordance with such an embodiment, as the lever plate  1  equal in number to the nozzle vane  2  are placed between the nozzle mount  4  and the link plate  3  in the turbine shaft axis, one edge side of the lever plate  1  is fixed to the nozzle shaft  02  of the nozzle vane  2 , the fitting pin section  3   a  protruding on the link plate  3  towards the lever plate side is fitted to the slot provided on the other edge side of the nozzle plate  1 , and punching is processed so that the punching portion  2   a  between the lever plate  1  and the shaft edge of the nozzle shaft  02  does not squeeze out over the surface of the lever plate  1 , the link plate  3  and the lever plate  1  can be assembled with the minimum gap, the distance between the link plate  3  and the nozzle mount  4  having the lever plate  1  sandwiched thereby is shortened and the length in the shaft axis of the adjustable nozzle mechanism  100  is shortened as well.  
         [0061]    Furthermore, as described above, erroneous operation of the adjustable nozzle mechanism  100  is prevented due to friction between the protruding part and the link plate  3  as the possible protrusion of the punched portion  2   a  of the nozzle shaft  02  from the side of the link plate is avoided.  
         [0062]    As mentioned above, according to this invention, In accordance with this invention, adjustment of the adjustable nozzle mechanism, that is, the position setup of the wing angle of the nozzle vane and the nozzle driving member, can be made in such extremely simple processes. In this process, the coupling hole provided at one edge of the lever plate and the coupling shaft at the end of the nozzle shaft are fitted after being set up geometrically so that the wing angle and the rotating angle of the link plate composing the nozzle driving member may be in the predetermined relation. The edge of the nozzle shaft is then punched into one of the chamfered portion having a larger diameter (chamfered portion) of the edge portion in order to be fixed on the lever plate. Then the lever plate and the link plate can be engaged to each other by engaging the pins with the slots provided at the end of the lever plate.  
         [0063]    With these simplified processes, adjustment of the adjustable nozzle mechanism during the nozzle assembly procedure is no longer required and therefore the assembling man-hours are decreased, particular assembling facilities such as the jigs are not needed, and as a result, assembling costs are decreased.  
         [0064]    Furthermore, as the adjustable nozzle mechanism according to this invention is configured in the manner that the one edge side of the joint members and the nozzle shaft are fixed upon the set geometrical relations between thereto and the nozzle driving member are joined to the other edge side of each joint member, the structure is simplified comparatively with the conventional art and the number of part category and parts itself are considerably decreased. Part costs are decreased accordingly.  
         [0065]    Furthermore, with this invention, configured such that the nozzle driving member is joined to the other edge of each joint member after these have been fitted on the condition that the wing angle of the nozzle vane and the rotating angle of the nozzle driving member had been set previously in the geometrical relation as required, and that adjustment of the adjustable nozzle mechanism, that is, the position setup of the wing angle of the nozzle vane and the nozzle driving member is available neither with a setting error that would arise in the conventional art from the variable setup for the total shutdown caused by the adjustment for the total shutdown position during nozzle assembling procedure using the multiple long slots, the stopper pin and jig, nor the total shutdown position of the adjustable nozzle mechanism should be determined primarily by the component parts, the setup herein of the adjustable nozzle mechanism is available to a high degree of accuracy without fear of influence by the dimensional accuracy of the nozzle assembly and the link assembly, as well as the enabling of the various requirement settings of the adjustable nozzle mechanism.  
         [0066]    Still furthermore, with the configuration mentioned in claims 5 and 3, configured such that the lever plates equal in number to the nozzle vanes are placed between the nozzle mount and the link plate in the turbine shaft axis, that the one edge of the lever plate is fixed on the nozzle shaft of the nozzle vane, that the fitting pin protruding toward the lever plate side in the link plate is fitted into the slots on the other edge of the lever plate, that the stopper between the lever plate and the edge of the nozzle shaft is processed with the use of the chamfered portion in order to prevent the stopper portion from squeezing out of the side face of the lever plate, It becomes possible to assemble the link plate and lever plate with a minimum distance, therefore, the distant between the link plate and the nozzle mount over the lever plate sandwiched thereby becomes shorter, and the length in the shaft axis of the adjustable nozzle mechanism is, as a result, shortened.  
         [0067]    Still furthermore, the punched portion using the chamfered portion avoids protrusion from the link plate side, and erroneous operation of the adjustable nozzle mechanism by the friction and interference between the link plate and the punched portion is also avoided.