Patent Publication Number: US-11391168-B2

Title: Gas turbine combustor and transition piece assembly

Description:
CLAIM OF PRIORITY 
     The present application claims priority from Japanese Patent application serial No. 2018-34887, filed on Feb. 28, 2018, the content of which is hereby incorporated by reference into this application. 
     TECHNICAL FIELD 
     The present invention concerns a gas turbine combustor and a transition piece assembly and, in particular, relates to the gas turbine combustor and the transition piece assembly which are favorable for the one that, on outer circumferences of coupled parts of a turbine stator vane of a gas turbine and a frame which is installed on an outlet part of a transition piece, a seal member for sealing so as not to flow compressed air from a compressor into the turbine side through a gap between the above-described coupled parts is installed. 
     BACKGROUND ART 
     In general, the gas turbine is configured by being equipped with the compressor, the combustor and the turbine and is made in such a manner that air compressed by the compressor is supplied to the combustor, the compressed air and a fuel supplied from other are mixed and burned to generate a combustion gas in the combustor and the combustion gas is expanded by the gas turbine. 
     A plurality of the combustors is installed in a circumferential direction of the turbine and a mixed fluid of the fuel and air is combusted in an upstream area of the transition piece in each combustor and the combustion gas is sent from the transition piece to a first-stage stator vane part on the gas turbine side. 
     Incidentally, since it is structured in such a manner that although the compressed air from the compressor is supplied to the combustor which is housed in a combustor casing, the compressed air is sent around the combustor including the transition piece, performs cooling and thereafter is supplied to the combustor, there has been a fear that the compressed air from the compressor might flow into the turbine side through a gap between the coupled parts of the transition piece and the first-stage stator vane part on the gas turbine side and operating efficiency of the gas turbine might be worsened due to a reduction in temperature of the combustion gas, useless consumption of the air which is not involved in combustion and so forth. 
     From such things, a seal member which seals the gap between the first-stage stator vane part on the turbine side and the outlet side of the transition piece is adopted on the coupled parts of the transition piece and the turbine side of the gas turbine combustor in such a manner that the compressed air from the compressor does not flow into the turbine side through a gap between the coupled parts and this seal member is generally mounted on the frame which is installed on the outlet part of the transition piece. 
     The ones that the seal member (including a floating seal material and a side seal material) which seals the gap between the first-stage stator vane part on the turbine side and the outlet side of the transition piece in such a manner that the compressed air from the above-described compressor does not flow into the turbine side through a gap between the coupled parts is mounted on the frame which is installed on the outlet part of the transition piece are described in Japanese Unexamined Patent Application Publication No. 2006-214671 (Patent Literature 1) and Japanese Unexamined Patent Application Publication No. 2003-193866 (Patent Literature 2). 
     In these Patent Literatures 1 and 2, it is disclosed that the transition piece is formed into a cylindrical shape at an inlet and into an inverted trapezoidal shape at an outlet, the frame of a shape which matches the inverted trapezoidal shape of the outlet of the transition piece is installed on the downstream side of this transition piece, the outlet side of the frame which is formed into the inverted trapezoidal shape is connected to the stator vane part on the turbine side and a frame seal groove is formed in an outer circumference on the outlet side of the aforementioned frame, the floating seal materials which are the seal members which float are engaged with top and bottom of this frame seal groove and the side seal materials which are the seal members are mounted on the both sides of the frame seal groove, and it is described that the floating seal material is engaged therewith with one end which is formed into a U-shape being inserted into the frame seal groove, an engagement side which extends at a right angle outward from an U-shaped leading end part is formed on the other end thereof and this engagement side is engaged therewith by being inserted into a stator vane seal groove which is formed in the first-stage stator vane part of the gas turbine which is located so as to face the frame on the downstream side of the transition piece. 
     SUMMARY OF THE INVENTION 
     Technical Problem 
     Incidentally, in the gas turbine combustors in the above-described Patent Literatures 1 and 2, when the floating seal material is made movable in the turbine circumferential direction and an axial direction with vibrations caused by combustion and flowing of the combustion gas, sliding occurs between the U-shaped leading end part of the floating seal material and the frame which is a mating-side member and, in particular, in a case where the vibration has generated in members which are inserted into the seal groove and built up by engagement as in Patent Literatures 1 and 2, there is a fear that wear may occur on contact parts of the mating members and wear damage may occur under a high temperature. 
     The present invention has been made in view of the above-described points and an object thereof is to provide a gas turbine combustor and a transition piece assembly which are able to suppress possible movement of the seal member in the turbine circumferential direction and the axial direction and to prevent occurrence of wear on the contact parts of the mating members even when there exist the vibrations caused by combustion and flowing of the combustion gas. 
     Solution to Problem 
     In order to attain the above-described object, a gas turbine combustor of the present invention is the gas turbine combustor which is equipped with a transition piece assembly of the combustor, the transition piece assembly of the combustor includes a transition piece in which a high-temperature combustion gas flows, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a stator vane part on the turbine side and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the aforementioned movement suppression mechanism and the aforementioned projection member fit together and thereby the aforementioned seal member is fixed to the frame. 
     In addition, in order to attain the above-described object, a transition piece assembly of the present invention is the transition piece assembly of a combustor which includes a transition piece in which a high-temperature gas flows, a frame which is installed on the downstream side (an outlet part) of the transition piece, and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the aforementioned coupled part, a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the aforementioned movement suppression mechanism and the aforementioned projection member fit together and thereby the aforementioned seal member is fixed to the frame. 
     Advantageous Effects of Invention 
     According to the present invention, possible movement of the seal member in the turbine circumferential direction and the axial direction can be suppressed and thereby occurrence of wear on the contact parts of the mating members can be prevented even when there exist the vibrations caused by combustion and flowing of the combustion gas. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a diagram illustrating an entire configuration of a gas turbine combustor according to an embodiment 1 of the present invention. 
         FIG. 2  is a perspective view illustrating the outlet side of a transition piece which is adopted in the embodiment 1 of the gas turbine combustor of the present invention by dismantling a seal member. 
         FIG. 3  is a diagram illustrating a joined part between a frame of the transition piece and a first-stage stator vane of the turbine which are adopted in the embodiment 1 of the gas turbine combustor of the present invention. 
         FIG. 4  is a partially enlarged diagram illustrating details of the joined part between the frame of the transition piece and the first-stage stator vane of the turbine in  FIG. 3 . 
         FIG. 5  is a plan view illustrating a state where a projection member which is installed on the frame of the transition piece in  FIG. 3  is fitted into a through-hole formed in a seal material. 
         FIG. 6  is a diagram illustrating the seal material which is adopted in the embodiment 1 of the gas turbine combustor of the present invention. 
         FIG. 7  is a plan view of  FIG. 6 . 
         FIG. 8  is a partially enlarged diagram illustrating details of a joined part between a frame of a transition piece and a first-stage stator vane of the turbine which are adopted in an embodiment 2 of the gas turbine combustor of the present invention. 
         FIG. 9  is a plan view illustrating a state where a projection member which is installed on the frame of the transition piece in  FIG. 8  is fitted into a through-hole formed in a seal material via a wear resistance piece. 
         FIG. 10  is a partially enlarged diagram illustrating details of a joined part between a frame of a transition piece and a first-stage stator vane of the turbine which are adopted in an embodiment 3 of the gas turbine combustor of the present invention. 
         FIG. 11  is a diagram illustrating a seal material which is adopted in the embodiment 3 of the gas turbine combustor of the present invention. 
         FIG. 12  is a plan view illustrating a state where a projection member which is installed on a frame of a transition piece in  FIG. 11  is fitted into a notch formed in the seal material. 
     
    
    
     DESCRIPTION OF EMBODIMENTS 
     In the following, a gas turbine combustor and a transition piece of the present invention will be described on the basis of illustrated embodiments. Incidentally, in the respective embodiments which will be described in the following, the same symbols are used for the same components. 
     Embodiment 1 
     An entire configuration of a power-plant-oriented gas turbine combustor is illustrated in  FIG. 1  as one example of the gas turbine combustor of the present invention. 
     As illustrated in  FIG. 1 , the gas turbine combustor is roughly configured by a transition piece  4  of the combustor in which a high-temperature combustion gas  107  flows, a transition piece flow sleeve  5  which is present around this transition piece  4  and includes the transition piece  4  therein, a flow passage  9  which is formed between this transition piece flow sleeve  5  and the transition piece  4  and through which high-temperature and high-pressure compressed air  100  which has been exhaled from a compressor  300  flows, a liner  6  which is connected to the transition piece  4  and a liner flow sleeve  7  which is connected to the transition piece flow sleeve  5 , is installed concentrically on an outer circumference of the liner  6  and thereby forms a gap through which a flow  102  of the compressed air passes. 
     Then, the compressed air  100  which has been introduced from the compressor  300  is introduced into a casing  2  through a diffuser  1  and flows into a gap (the flow passage  9 ) which is formed by the transition piece flow sleeve  5  and the transition piece  4  (illustrated by an arrow  20 ). 
     That is, the compressed air  100  which has been introduced into the cashing  2  through the diffuser  1  becomes a flow  20  which enters the flow passage  9  which is formed by the transition piece flow sleeve  5  and the transition piece  4  through an opening formed in a downstream-side end of the transition piece flow sleeve  5 . 
     Thereafter, the compressed air  100  which has flown into the flow passage  9  becomes a flow  102  which passes through the gap between the liner  6  and the liner flow sleeve  7  which is installed concentrically on the outer circumference of the liner  6  as indicated by a flow  101 . Then, the flow is reversed, becomes flows  103 ,  104  which is introduced into a burner part, is mixed with a fuel supplied from fuel systems  200 ,  201 , forms flames  105 ,  106  in a combustion chamber  8  in the liner  6  and becomes a high-temperature and high-pressure combustion gas  107 . Thereafter, although it becomes a combustion gas  108  which is introduced from the transition piece  4  into a turbine  301 , in the gas turbine, an output is obtained from a power generator  302  by converting an amount of work that the high-temperature and high-pressure combustion gas  108  generates when it adiabatically expands into axial rotation force in the turbine  301 . Incidentally, the illustrated combustor is configured by a premixed combustion burner (a main burner) and a diffusion combustion burner (a pilot burner), the fuel system which supplies the fuel to the premixed burner is displayed as the symbol  201  and the fuel system which supplies the fuel to the diffusion combustion burner is displayed as the symbol  200 . 
     Incidentally, although the compressed air  100  from the compressor  300  is supplied to the combustor, it is structured in such a manner that the compressed air  100  is sent around the combustor including the transition piece  4 , performs cooling and thereafter is supplied to the combustor. Then, when the compressed air  100  from the compressor  300  leaks to the turbine side through a gap between coupled parts of the transition piece  4  and a first-stage stator vane part  14  on the turbine side (see  FIG. 3 ), a leaking portion thereof does not contribute to cooling of the transition piece  4  and generation of the combustion gas  107  and becomes a factor of lowering operating efficiency of the gas turbine. Therefore, a seal member  10  (see  FIG. 2  and  FIG. 3 ) which seals the gap between the first-stage stator vane part  14  on the turbine side and the outlet side of the transition piece  4  is adopted on the coupled parts of the transition piece  4  and the turbine side of the gas turbine combustor in such a manner that the compressed air  100  from the compressor  100  does not flow out to the turbine side through a gap between the coupled parts and, in general, this seal member  10  is mounted on a frame  11  (see  FIG. 2  and  FIG. 3 ) which is installed on the outlet part of the transition piece  4 . 
     The seal member  10  and the frame  11  will be described by using  FIG. 2 .  FIG. 2  illustrates details of the outlet side of the transition piece  4 . 
     As illustrated in  FIG. 2 , the seal member  10  includes floating seal materials  10   a ,  10   b  and side seal materials  10   c ,  10   d , the transition piece  4  is formed into a cylindrical shape at an inlet (the combustor liner side) of the combustion gas and into an inverted trapezoidal shape at an outlet (the turbine side), the frame  11  of a shape which matches the inverted trapezoidal shape of the outlet of the transition piece  4  is installed on the downstream side (the turbine side) of this transition piece  4  and the outlet side of the frame  11  which is formed into the inverted trapezoidal shape is connected to the first-stage stator vane part  14  (a turbine inlet part) on the turbine side. Then, the floating seal materials  10   a ,  10   b  are mounted on the upper and lower sides (the radial-direction inner side and outer side) of this frame  11  and the side seal materials  10   c ,  10   d  are mounted on the lateral sides thereof. 
     Next, a structure of fixing the seal member  10  to the frame  11  in the present embodiment will be described by using  FIG. 3 ,  FIG. 4 ,  FIG. 5 ,  FIG. 6  and  FIG. 7 . 
     As illustrated in  FIG. 3  and  FIG. 4 , in the present embodiment, a projection member  12  (see  FIG. 5 ) which extends outward and inward (a top-bottom direction in  FIG. 3  and  FIG. 4 ) in a radius direction of the transition piece  4  is provided on an outer circumference of the frame  11  and a through-hole  13  (an opening of a shape corresponding to an outer shape of the projection member  12  viewing from an extending direction) which matches this projection member  12  is provided in the floating seal materials  10   a ,  10   b , the projection member  12  is fitted into the through-hole  13  in the floating seal materials  10   a ,  10   b  and thereby the floating seal materials  10   a ,  10   b  are fixed. 
     The above-described floating seal materials  10   a ,  10   b  are configured by fix parts  10   a   1 ,  10   b   1  which are fixed to the frame  11  and seal parts  10   a   2 ,  10   b   2  which seal between the coupled parts of the transition piece  4  and the turbine. The fix parts  10   a   1 ,  10   b   1  are formed into, for example, U-shapes such as those illustrated in  FIG. 3 ,  FIG. 4  which are shapes which arcuately curve along protruded parts which are provided on the radius-direction inner side and outer side of the frame  11 . In addition, the through-hole  13  is formed in the fix parts  10   a   1 ,  10   b   1  at positions where it corresponds to the aforementioned projection member  12  when mounted on the frame  11 . In examples illustrated in  FIG. 3 ,  FIG. 4 , the through-hole  13  is formed at positions on top parts of the fix parts  10   a   1 ,  10   b   1  which curve into the U-shapes. 
     In addition, the seal parts  10   a   2 ,  10   b   2  which seal the coupled parts of the transition piece  4  and the turbine inlet are connected to the downstream sides (right-hand sides of  FIG. 3 ,  FIG. 4 ) of the fix parts  10   a   1 ,  10   b   1 . These seal parts  10   a   2 ,  10   b   2  are engagement pieces which bend at a right angle from terminal parts on the downstream sides of the U-shaped fix parts  10   a   1 ,  10   b   1  and extend to the downstream sides along an outer surface of the outlet part of the frame  11 . 
     Then, a seal groove  14   a  whose opening part is formed on the upstream side of a combustion gas flowing direction is provided in a face which faces the frame  11  on the turbine side. This seal groove  14   a  is formed in the face which faces the frame  11  by extending in a circumferential direction of the turbine. The downstream sides of the seal parts  10   a   2 ,  10   b   2  of the floating seal materials  10   a ,  10   b  are inserted into the seal groove  14   a . The seal parts  10   a   2 ,  10   b   2  are fitted into this seal groove  14   a  and thereby a gap in a bonded part which is formed along the circumferential direction of the turbine is sealed. In addition, since the projection member  12  is fitted into the through-hole  13 , movement of the floating seal materials  10   a ,  10   b  relative to the circumferential direction of the turbine can be restricted. 
     Thereby, it is structured in such a manner that the compressed air  100  is prevented from flowing into the turbine flow passage through an axial-direction gap between the coupled parts of the frame  11  on the downstream side of the transition piece  4  and the first-stage stator vane part  14  (see  FIG. 3 ) on the gas turbine side and the floating seal materials  10   a ,  10   b  do not fall off. 
     The shape of the above-described projection member q 12  is, for example, a rectangular parallelepiped shape and is the one that rounding is performed on a side-face side thereof. In addition, even when the shape of the projection member  12  is columnar and the number of the projection members  12  is two or more, the effect of the present embodiment is not impaired. 
     Incidentally, the turbine circumferential-direction inner circumference side (the ventral side) and outer circumference side (the dorsal side) of the frame  11  illustrated in  FIG. 2  are formed into shapes which bend in a circular arc so as to match the flow passage in which the first-stage stator vane  14  on the turbine side is installed. 
     Owing to the configuration of the present embodiment like this, that is, owing to fitting of the projection member  12  provided on the frame  11  and the through-hole  13  formed in the floating seal materials  10   a ,  10   b , possible movement of the floating seal materials  10   a ,  10   b  in the turbine circumferential direction and axial direction is suppressed. 
     In addition, since the turbine circumferential-direction possible movement of the floating seal materials  10   a ,  10   b  is determined only by fitting faces of the through-hole  13  and the projection member  12 , a turbine circumferential-direction possible movement range, that is, position accuracy of the floating seal materials  10   a ,  10   b  can be managed only by management of accuracy of the fitting faces of the through-hole  13  and the projection member  12 . 
     Therefore, according to the configuration of the present embodiment, suppression of amounts of the turbine circumferential-direction possible movement of the floating seal materials  10   a ,  10   b  is facilitated and it is advantageous for maintaining the position accuracy high. 
     In addition, when incorporating the transition piece  4  into the casing  2  of the gas turbine, even when a space in the casing  2  is small, the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  can be incorporated thereinto by mounting in advance the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  on the frame  11 . 
     At this time, gaps that tolerance for incorporation is taken into consideration in the turbine circumferential direction are necessary between the adjacent floating seal materials  10   a ,  10   b  in order not to allow contact of the mating floating seal materials  10   a ,  10   b  of the adjacent combustor cans. 
     Since in the present embodiment, since the position accuracy of the floating seal materials  10   a ,  10   b  in the turbine circumferential direction can be maintained high by holding the floating seal materials  10   a ,  10   b  by fitting of the projection member  12  and the through-hole  13 , the turbine circumferential-direction gaps between the adjacent floating seal materials  10   a ,  10   b  can be made small. As a result, sealability can be maintained high and low NOx and backfire prevention can be realized. 
     Further, the possible movement amounts of the floating seal materials  10   a ,  10   b  are made small and thereby sliding distances of the floating seal materials  10   a ,  10   b  relative to the frame  11  become small. Therefore, amounts of wear on contact faces of the floating seal materials  10   a ,  10   b  and the frame  11  can be reduced and life elongation of the floating seal materials  10   a ,  10   b  and the frame  11  can be realized. 
     According to the present embodiment like this, it is a matter of course that occurrence of wear on contact parts of mating members can be prevented by suppressing the possible movement of the floating seal materials  10   a ,  10   b  in the turbine circumferential direction and axial direction even when there exist vibrations caused by combustion and flowing of the combustion gas, and the turbine circumferential-direction position accuracy of the floating seal materials  10   a ,  10   b  can be maintained high, there is an effect of lowering NOx and preventing backfire owing to easy assembly and high seal performance and further the transmission piece of the gas turbine combustor which attains life elongation can be realized. 
     Embodiment 2 
     Next, the embodiment 2 of the gas turbine combustor of the present invention will be described by using  FIG. 8  and  FIG. 9 . 
     In the present embodiment illustrated in the drawings, it is characterized in that the projection member  12  is inserted into the through-hole  13  in the floating seal material  10   a  ( 10   b ) via a wear resistance piece  15  and thereby the floating seal material  10   a  ( 10   b ) is fixed. 
     Specifically, it has the projection member  12  which extends in the radius direction (the top-bottom direction in  FIG. 8 ) of the transition piece  4 , a radius-direction leading end part is made thinner than the frame  11  side and thereby a stepped part  12   c  is formed on this projection member  12 , a male screw  12   a  is threaded in the leading end part of the projection member  12 , a nut  16  is engaged with the male screw  12   a  portion and it is fastened therewith and thereby the floating seal material  10   a  ( 10   b ) is fixed to the stepped part  12   c  of the projection member  12  via the wear resistance piece  15  which is inserted into the leading end part of the projection member  12 . 
     Further, a face  15   a  which prevents falling of the floating seal material  10   a  ( 10   b ) is formed on a face of the wear resistance piece  15  which is in contact with the stepped part  12   c  of the projection member  12  on the side opposite to a face which is fastened with the nut  16 . 
     In addition, also in the present embodiment, similarly to the embodiment 1, the transition piece  4  is formed into the cylindrical shape at the inlet (the combustor liner side) of the combustion gas and into the inverted trapezoidal shape at the outlet (the turbine side), the frame  11  of the shape which matches the inverted trapezoidal shape of the outlet of the transition piece  4  is installed on the downstream side (the turbine side) of this transition piece  4  and the outlet side of the frame  11  which is formed into the inverted trapezoidal shape is connected to the first-stage stator vane part  14  (the turbine inlet part) on the turbine side. Then, the floating seal materials  10   a  ( 10   b ) are mounted on the upper and lower sides (the radial-direction inner side and outer side) of this frame  11  and the side seal materials  10   c ,  10   d  are mounted on the lateral sides thereof. 
     In addition, the floating seal material  10   a  ( 10   b ) of the present embodiment is configured by the fix part  10   a   1  ( 10   b   1 ) which is fixed to the frame  11  and the seal part  10   a   2  ( 10   b   2 ) which seals between the coupled parts of the transition piece  4  and the turbine similarly to the embodiment 1. The fix part  10   a   1  ( 10   b   1 ) is formed into, for example, the U-shape such as that illustrated in  FIG. 8  which is the shape which arcuately curves along the protruded part which is provided on the radius-direction inner side and outer side of the frame  11 . In addition, the through-hole  13  is formed in the fix part  10   a   1  ( 10   b   1 ) at the position where it corresponds to the aforementioned projection member  12  when mounted on the frame  11 . In an example in  FIG. 8 , the through-hole  13  is formed at the position on the top part of the fix part  10   a   1  ( 10   b   1 ) which curves into the U-shape. 
     In addition, the seal part  10   a   2  ( 10   b   2 ) which seals the coupled parts of the transition piece  4  and the turbine inlet is connected to the downstream side (the right-hand side of  FIG. 8 ) of the fix part  10   a   1  ( 10   b   1 ). This seal part  10   a   2  ( 10   b   2 ) is the engagement piece which bends at a right angle from the terminal part on the downstream side of the U-shaped fix part  10   a   1  ( 10   b   1 ) and extends to the downstream side along the outer surface of the outlet part of the frame  11 . 
     Then, the seal groove  14   a  whose opening part is formed on the upstream side of the combustion gas flowing direction is provided in the face which faces the frame  11  on the turbine side. This seal groove  14   a  is formed in the face which faces the frame  11  by extending in the turbine circumferential direction. The downstream side of the seal part  10   a   2  ( 10   b   2 ) of the floating seal material  10   a  ( 10   b ) is inserted into the seal groove  14   a . The seal part  10   a   2  ( 10   b   2 ) is fitted into this seal groove  14   a  and thereby the gap in the bonded part which is formed along the turbine circumferential direction is sealed. In addition, since the projection member  12  is fitted into the through-hole  13 , the movement of the floating seal material  10   a  ( 10   b ) relative to the turbine circumferential direction can be restricted. 
     Thereby, it is structured in such a manner that the compressed air  100  is prevented from flowing into the turbine flow passage through the axial-direction gap between the coupled parts of the frame  11  on the downstream side of the transition piece  4  and the first-stage stator vane part  14  (see  FIG. 8 ) on the gas turbine side and the floating seal material  10   a  ( 10   b ) does not fall off. 
     Further, a root part  12   b  of the projection member  12  in the present embodiment is formed into a rectangular parallelepiped shape and rounding is performed on a corner of a side face of this rectangular parallelepiped root part  12   b  of the projection member  12 . 
     The possible movement of the floating seal material  10   a  ( 10   b ) in the turbine circumferential direction and axial direction is determined only by fitting faces of the through-hole  13  formed in the above-described floating seal material  10   a  ( 10   b ) and the wear resistance piece  15  and the fitting faces of the wear resistance piece  15  and the projection member  12 . 
     Therefore, since the turbine circumferential-direction possible movement range, that is, the position accuracy of the floating seal material  10   a  ( 10   b ) can be managed only by management of the accuracy of the fitting faces of the aforementioned three members (the wear resistance piece  15 , the projection member  12 , the floating seal material  10   a  ( 10   b )), suppression of the amount of the turbine circumferential-direction possible movement of the floating seal material  10   a  ( 10   b ) is facilitated by making into the structure of the present embodiment and it is advantageous for maintaining the position accuracy high. 
     In addition, when incorporating the transition piece  4  into the casing  2  of the gas turbine, even when the space in the casing  2  is small, the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  can be incorporated thereinto by mounting in advance the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  on the frame  11 . 
     At this time, the gaps that the tolerance for incorporation is taken into consideration in the turbine circumferential direction are necessary between the adjacent floating seal materials  10   a ,  10   b  in order not to allow contact of the mating floating seal materials  10   a ,  10   b  of the adjacent combustor cans. 
     In the present embodiment, the position accuracy of the floating seal material  10   a  ( 10   b ) in the turbine circumferential direction can be maintained high by holding the floating seal materials  10   a  ( 10   b ) by fitting of the projection member  12  and the wear resistance piece  15  and the through-hole  13  and thereby the turbine circumferential-direction gap between the adjacent floating seal materials  10   a  ( 10   b ) can be made small. As a result, the sealability can be maintained high and the low NOx and the backfire prevention can be realized. 
     Further, the possible movement amount is made small by making the gap between the floating seal material  10   a  ( 10   b ) and the wear resistance piece  16  and the gap between the wear resistance piece  15  and the projection member  12  small and thereby the sliding distance of the floating seal material  10   a  ( 10   b ) relative to the frame  11  becomes small. 
     Therefore, the amounts of wear on the contact faces of the floating seal material  10   a  ( 10   b ) and the frame  11  can be reduced and the life elongation of the floating seal material  10   a  ( 10   b ) and the frame  11  can be realized. 
     In addition, the face  15   a  for preventing falling of the floating seal material  10   a  ( 10   b ) is formed on the wear resistance piece  15  and thereby falling of the floating seal material  10   a  ( 10 B) can be prevented when incorporating the transition piece  4  and incorporation of the transition piece  4  is more facilitated. 
     In addition, since the wear resistance piece  15  is fixed with the male screw  12   a  and the nut  16 , detachment of the floating seal material  10   a  ( 10   b ) and the wear resistance piece  15  is easy in comparison with fixing by welding. In particular, on a site of the gas turbine, the floating seal material  10   a  ( 10   b ) and the wear resistance piece  15  can be replaced with other ones with no need of a welding technology and short-time and low-cost maintenance can be realized. 
     In addition, since contact between the projection member  12  and the floating seal material  10   a  ( 10   b ) can be prevented by the wear resistance piece  15  and a contact area of a member which is in contact with the projection member  12  can be made large in comparison with a case of the floating seal material  10   a  ( 10   b ), a surface pressure on the fitting face of the projection member  12  can be made small, an amount of wear damage on the projection member  12  is reduced and the life thereof can be elongated. 
     Further, it is desirable to select a combination of materials of the wear resistance piece  15 , the floating seal material  10   a  ( 10   b ) which is advantageous for wear resistance and, for example, the combination of mating HS25 and HS25 is given. HS25 is carbide-precipitation-strengthened type cobalt-based alloy (L605, AMS-5537/AMS-5796, UNS R30605). In addition, it is also desirable to select the combination which is advantageous for the wear resistance as the combination of the materials of the wear resistance piece  15  and the projection member  12  and, for example, the mating HS25 and HS25 are given. 
     According to the present embodiment like this, it is a matter of course that occurrence of the wear on the contact parts of the mating members can be prevented by suppressing the possible movement of the floating seal materials  10   a ,  10   b  in the turbine circumferential direction and axial direction even when there exist the vibrations caused by combustion and flowing of the combustion gas, and the turbine circumferential-direction position accuracy of the floating seal materials  10   a ,  10   b  can be maintained high, there is the effect of lowering NOx and preventing the backfire owing to the easy assembly and the high seal performance and further the transmission piece of the gas turbine combustor which attains the life elongation can be realized. 
     Embodiment 3 
     Next, the embodiment 3 of the gas turbine combustor of the present invention will be described by using  FIG. 10 ,  FIG. 11  and  FIG. 12 . 
     In the present embodiment illustrated in the drawings, it is characterized in that a projection member  17  which extends to the combustor liner side (a left-hand direction in  FIG. 10 ) which is the upstream side of a gas distribution direction of the transition piece  4  is provided on the outer circumference of the frame  11 , a notch  18  which matches this projection member  17  is formed in the floating seal material  10   a  ( 10   b ), the projection member  17  is fitted into the notch  18  in the floating seal material  10   a  ( 10   b ) and thereby the floating seal material  10   a  ( 10   b ) is fixed. 
     In addition, in the present embodiment, a bolt-use hole is formed in a leading end of the projection member  17  and further it is equipped with a fall prevention piece  19  that one side covers part of the floating seal material  10   a  ( 10   b ) and thereby prevents falling of the floating seal material  10   a  ( 10   b ) in a radius direction (an upward direction in  FIG. 10 ) of the transition piece  4  and other side end is fixed together with the projection member  17  with a bolt and a nut  21  via the bolt-use hole. 
     Incidentally, the projection member  17  which extends to the combustor liner side of the transition piece  4  is formed integrally with the frame  11  or is fixed to the frame  11  by welding. 
     In addition, also in the present embodiment, similarly to the embodiments 1 and 2, the transition piece  4  is formed into the cylindrical shape at the inlet (the combustor liner side) of the combustion gas and into the inverted trapezoidal shape at the outlet (the turbine side), the frame  11  of the shape which matches the inverted trapezoidal shape of the outlet of the transition piece  4  is installed on the downstream side (the turbine side) of this transition piece  4  and the outlet side of the frame  11  which is formed into the inverted trapezoidal shape is connected to the first-stage stator vane part  14  (the turbine inlet part) on the turbine side. Then, the floating seal materials  10   a  ( 10   b ) are mounted on the upper and lower sides (the radial-direction inner side and outer side) of this frame  11  and the side seal materials  10   c ,  10   d  are mounted on the lateral sides thereof. 
     In addition, the above-described floating seal material  10   a  ( 10   b ) is configured by the fix part  10   a   1  ( 10   b   1 ) which is fixed to the frame  11  and the seal part  10   a   2  ( 10   b   2 ) which seals between the coupled parts of the transition piece  4  and the turbine similarly to the embodiments 1 and 2. The fix part  10   a   1  ( 10   b   1 ) is formed into, for example, the U-shape such as that illustrated in  FIG. 10  which is the shape which arcuately curves along the protruded part which is provided on the radius-direction outer side and inner side of the frame  11 . In addition, the notch  18  is formed in the fix part  10   a   1  ( 10   b   1 ) at the position where it corresponds to the aforementioned projection member  17  when mounted on the frame  11 . In an example in  FIG. 10 , the notch  18  is formed at a lateral position of the fix part  10   a   1  ( 10   b   1 ) which curves into the U-shape. 
     In addition, the seal part  10   a   2  ( 10   b   2 ) which seals the coupled parts of the transition piece  4  and the turbine inlet is connected to the downstream side (the right-hand side of  FIG. 10 ) of the fix part  10   a   1  ( 10   b   1 ). This seal part  10   a   2  ( 10   b   2 ) is the engagement piece which bends at a right angle from the terminal part on the downstream side of the U-shaped fix part  10   a   1  ( 10   b   1 ) and extends to the downstream side along the outer surface of the outlet part of the frame  11 . 
     Then, the seal groove  14   a  whose opening part is formed on the upstream side of the combustion gas flowing direction is provided in the face which faces the frame  11  on the turbine side. This seal groove  14   a  is formed in the face which faces the frame  11  by extending in the turbine circumferential direction. The downstream side of the seal part  10   a   2  ( 10   b   2 ) of the floating seal material  10   a  ( 10   b ) is inserted into the seal groove  14   a . The seal part  10   a   2  ( 10   b   2 ) is fitted into this seal groove  14   a  and thereby the gap in the bonded part which is formed along the turbine circumferential direction is sealed. In addition, since the projection member  17  is fitted into the notch  18 , the movement of the floating seal material  10   a  ( 10   b ) relative to the turbine circumferential direction can be restricted. 
     Thereby, it is structured in such a manner that the compressed air  100  is prevented from flowing into the turbine flow passage through the axial-direction gap between the coupled parts of the frame  11  on the downstream side of the transition piece  4  and the first-stage stator vane part  14  (see  FIG. 10 ) on the gas turbine side and the floating seal material  10   a  ( 10   b ) does not fall off. 
     As described above, the bolt-use hole used for attaching the fall prevention piece  19  is provided in the leading end of the projection member  17 , the fall prevention piece  19  is fixed together with the projection member  17  with the bolt  22  and the nut  21  via the bolt-use hole and falling of the floating seal material  10   a  ( 10   b ) in the radial direction is prevented by the fall prevention piece  19 . 
     Incidentally, the floating seal material  10   a  ( 10   b ) may be pressed against the first-stage stator vane part  14  side on the axial-direction turbine side by the fall prevention piece  19  so as to bring the floating seal material  10   a  ( 10   b ) into contact with an axial-direction combustor-side side face  11   b  of the frame  11 . 
     In the present embodiment, the turbine circumferential-direction possible movement of the floating seal material  10   a  ( 10   b ) is suppressed by fitting of the projection member  17  and the notch  18  formed in the floating seal material  10   a  ( 10   b ). 
     That is, since the turbine circumferential-direction possible movement of the floating seal material  10   a  ( 10   b ) is determined only by the fitting faces of the notch  18  formed in the floating seal material  10   a  ( 10   b ) and the projection member  17 , the turbine circumferential-direction possible movement range, that is, the position accuracy of the floating seal material  10   a  ( 10   b ) can be managed only by management of the accuracy of the fitting faces of the notch  18  and the projection member  17 . 
     Therefore, suppression of the amount of the turbine circumferential-direction possible movement of the floating seal material  10   a  ( 10   b ) is facilitated by forming into the structure of the present embodiment and it is advantageous for maintaining the position accuracy high. 
     In addition, when incorporating the transition piece  4  into the casing  2  of the gas turbine, even when the space in the casing  2  is small, the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  can be incorporated thereinto by mounting in advance the floating seal materials  10   a ,  10   b  and the side seal materials  10   c ,  10   d  on the frame  11 . 
     At this time, the gaps that the tolerance for incorporation is taken into consideration in the turbine circumferential direction are necessary between the adjacent floating seal materials  10   a ,  10   b  in order not to allow contact of the mating floating seal materials  10   a ,  10   b  of the adjacent combustor cans. 
     Since in the present embodiment, the floating seal material  10   a  ( 10   b ) is held by fitting of the projection member  17  and the notch  18 , the position accuracy of the floating seal material  10   a  ( 10   b ) in the turbine circumferential direction can be maintained high and the turbine circumferential-direction gap between the adjacent floating seal materials  10   a  ( 10   b ) can be made small. As a result, the sealability can be maintained high and the low NOx and the backfire prevention can be realized. 
     Further, the possible movement amount of the floating seal material  10   a  ( 10   b ) is made small and thereby the sliding distance of the floating seal material  10   a  ( 10   b ) relative to the frame  11  becomes small. Therefore, the amounts of wear on the contact faces of the floating seal material  10   a  ( 10   b ) and the frame  11  can be reduced and the life elongation of the floating seal material  10   a  ( 10   b ) and the frame  11  can be realized. 
     In addition, since the floating seal material  10   a  ( 10   b ) does not fall off by the fall prevention piece  19  when incorporating the transition piece  4 , incorporation of the transition piece  4  is more facilitated. 
     In addition, since the fall prevention piece  19  is fixed to the leading end of the projection member  17  together with the projection member  17  with the bolt  22  and the nut  21 , detachment of the fall prevention piece  19  and the floating seal material  10   a  ( 10   b ) is easy in comparison with fixing by welding. In particular, on the site of the gas turbine, the floating seal material  10   a  ( 10   b ) and the fall prevention piece  19  can be replaced with other ones with no need of the welding technology and the short-time and low-cost maintenance can be realized. 
     In addition, when the floating seal material  10   a  ( 10   b ) is pressed against the first-stage stator vane part  14  side on the axial-direction turbine side by the fall prevention piece  19  so as to bring the floating seal material  10   a  ( 10   b ) into contact with the frame  11 , the axial-direction possible movement of the floating seal material  10   a  ( 10   b ) relative to the frame  11  is suppressed. 
     Thereby, since the distance of sliding of the floating seal material  10   a  ( 10   b ) relative to the frame  11  becomes small, the wear amounts of the floating seal material  10   a  ( 10   b ) and the frame  11  become small and thereby the life elongation of the floating seal material  10   a  ( 10   b ) and the frame  11  can be realized. 
     In addition, in a case where the floating seal material  10   a  ( 10   b ) is pressed against the first-stage stator vane part  14  side on the axial-direction turbine side by the fall prevention piece  19  so as to bring the floating seal material  10   a  ( 10   b ) into contact with the frame  11 , since the gap on the axial-direction combustor liner side is closed in the gaps between the frame  11  and the floating seal material  10   a  ( 10   b ), a leak path of the compressed air  100  becomes small. Thereby, the sealability is improved and the low NOx and the backlash prevention can be realized. 
     Further, it is desirable to select the combination of the materials of the projection member  17  and the floating seal material  10   a  ( 10   b ) which is advantageous for the wear resistance and, for example, the combination of the mating HS25 and HS25 is given. 
     According to the present embodiment like this, it is a matter of course that even when there exist the vibrations caused by combustion and flowing of the combustion gas, occurrence of the wear on the contact parts of the mating members can be prevented by suppressing the possible movement of the floating seal materials  10   a ,  10   b  in the turbine circumferential direction and axial direction, and the turbine circumferential-direction position accuracy of the floating seal materials  10   a ,  10   b  can be maintained high, there is the effect of lowering NOx and preventing the backfire owing to the easy assembly and the high seal performance and further the transmission piece of the gas turbine combustor which attains the life elongation can be realized. 
     Incidentally, the present invention is not limited to the above-described embodiments and various modified examples are included. For example, the above-described embodiments are the ones described in detail for the purpose of comprehensively describing the present invention and it is not necessarily limited to the one which is equipped with all the configurations which have been described. In addition, it is possible to replace part of a configuration of one embodiment with a configuration of another embodiment and it is also possible to add a configuration of another embodiment to a configuration of one embodiment. In addition, it is possible to add, delete and replace another configuration to, from and with part of one configuration of each embodiment. 
     REFERENCE SIGNS LIST 
       1  . . . diffuser,  2  . . . casing,  4  . . . transition piece,  5  . . . transition piece flow sleeve,  6  . . . liner,  7  . . . liner flow sleeve,  8  . . . combustion chamber,  9  . . . flow passage formed by the transition piece and the transition piece flow sleeve,  10  . . . seal member,  10   a ,  10   b  . . . floating seal material,  10   c ,  10   d  . . . side seal material,  10   a   1 ,  10   b   1  . . . fix part of the floating seal material,  10   a   2 ,  10   b   2  . . . seal part of the floating seal material,  11  . . . frame,  12 ,  17  . . . projection member,  12   a  . . . male screw of the projection member,  12   b  . . . root part of the projection member,  12   c  . . . stepped part of the projection member,  13  . . . through-hole,  14  . . . turbine-side first-stage stator vane part,  14   a  . . . seal groove,  15  . . . wear resistance piece,  15   a  . . . face of the wear resistance piece for preventing falling of the floating seal material,  16 ,  21  . . . nut,  18  . . . notch,  19  . . . fall prevention piece,  22  . . . bolt,  100  . . . compressed air,  105 ,  106  . . . flame,  107 ,  108  . . . combustion gas,  200 ,  201  . . . fuel system,  300  . . . compressor,  301  . . . turbine, and  302  . . . power generator.