JP2008031870A - Seal structure of gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide seal structure of a gas turbine surely suppressing leakage of air from a clearance of a tail pipe seal to the inside of a tail pipe, by properly installing the tail pipe seal. <P>SOLUTION: In the gas turbine, a plurality of combustors are arranged in a circumferential direction of the turbine, fuel is supplied to compressed air and burnt by the plurality of combustors, and generated combustion gas is supplied to stator blades and moving blades of the turbine so as to acquire rotation power. The gas turbine comprises: the tail pipe seals 50 connecting tail pipes 32 of the plurality of combustors with shrouds 41 of the stator blades and constituted of divided parts 53 which is formed by being circumferentially divided into a plurality of pieces; first seal plates 61 inserted into neighboring divided parts 53 of each tail pipe seal 50 assembled to the tail pipe 32 or the shroud 41 so as to connect them; and a falling-off prevention means 70 preventing slipping off of the first seal plates 61 from the tail pipe seal 50. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a gas turbine seal structure, and more particularly to a gas turbine seal structure in a tail cylinder seal that connects a plurality of combustor tail cylinders and stationary blade shrouds.

  The gas turbine is composed of a compressor, a combustor, and a turbine, and the air taken in from the air intake port is compressed by the compressor to become high-temperature / high-pressure compressed air. The fuel is supplied and burned, and the high-temperature and high-pressure combustion gas drives the turbine, and the generator connected to the turbine through the rotor is driven. In this case, the turbine is configured by alternately arranging a plurality of stationary blades and moving blades in the vehicle interior, and combustion gas is supplied to the plurality of stationary blades and moving blades. By driving, the output shaft connected to the generator is driven to rotate. The combustion gas that has driven the turbine is released to the atmosphere after the dynamic pressure is converted to static pressure by the diffuser in the exhaust casing.

  In such a gas turbine, a plurality of combustors are arranged in the circumferential direction of the turbine, and each is provided with a tail cylinder that supplies combustion gas to a stationary blade. A transition piece seal is provided between the opening on the stationary blade side of the transition piece and the shroud that supports the blade portion of the stationary blade. The transition piece seal is provided in an annular shape along a plurality of combustors arranged in the circumferential direction of the turbine, and connects the transition piece of the combustor and the shroud of the stationary blade. In addition, as such a conventional tail pipe seal, the tail pipe seal is divided into a plurality of parts in the circumferential direction, thereby concentrating stress due to thermal expansion and vibration of the combustor tail pipe and the stationary blade shroud. There is a tail pipe seal to avoid.

  However, in the gas turbine seal structure as described above, compressed air from the compressor is supplied to the combustor. This compressed air is once sent around the combustor including the combustor tail and cooled. After that, the compressed air flows into the tail tube through the gap between the divided tail tube seals, and waste of air that is not involved in temperature reduction of combustion gas or combustion. In order to reduce the amount of air leaked into the transition piece, the seal plate between the opposed end faces of the divided transition piece seals may have deteriorated the operation efficiency of the gas turbine due to consumption or the like. Was fitted.

  In addition, as a structure which connects the member divided | segmented into the circumferential direction like the above-mentioned tail pipe seal, and comprises an annular member, for example like the stationary blade attachment mechanism of the gas turbine of patent document 1 In each of the divided high-pressure turbine nozzles, there is a structure in which a seal plate groove is formed in an end surface facing each circumferential direction of each high-pressure turbine nozzle, and the seal plate is fitted into the seal plate groove to form a ring shape.

JP-A-8-35401

  However, in the stationary blade mounting mechanism for a gas turbine described in Patent Document 1 described above, an annular high pressure turbine nozzle is configured by inserting a seal plate into the opposed end faces of each divided high pressure turbine nozzle and sequentially connecting them. Therefore, it becomes difficult to insert the last one. For this reason, the seal plate that connects the last pair of the high-pressure turbine nozzles divided into a plurality of parts cannot be assembled properly, and this seal plate may fall off. Even if applied to the structure, after all, air leakage into the transition piece cannot be properly suppressed.

  Then, this invention aims at providing the seal structure of the gas turbine which can suppress reliably the leakage of the air from the clearance gap of a tail cylinder seal in a tail cylinder by mounting | wearing a tail cylinder seal appropriately. .

  To achieve the above object, the gas turbine seal structure according to the first aspect of the present invention includes a plurality of combustors arranged in the circumferential direction of the turbine, and the plurality of combustors supply fuel to the compressed air for combustion. In the gas turbine that obtains rotational power by supplying the generated combustion gas to the stationary blades and moving blades of the turbine, the tail cylinders of the plurality of combustors and the shrouds of the stationary blades are connected together and plural in the circumferential direction. A first seal plate that connects the two by inserting into the adjacent divided portion of the transition piece seal assembled to the transition piece or the shroud; A drop prevention means capable of preventing the first seal plate from falling off the tail tube seal is provided.

  In the gas turbine seal structure according to the second aspect of the present invention, at least one pair of the adjacent divided portions has a pair of slide grooves that allow the first seal plate to move along the flow direction of the combustion gas. The drop-off prevention means is fixed to the tail tube seal and is capable of preventing the movement of the first seal plate by contacting the first seal plate.

  In the gas turbine seal structure according to a third aspect of the present invention, the transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and the pair of recesses is formed before the attachment of the transition piece seal. A second seal plate that is fitted and fixed is provided, and the first seal plate can be fitted into the pair of slide grooves after the tail tube seal is assembled.

  In the gas turbine seal structure according to a fourth aspect of the present invention, the transition piece seal has a stationary blade side fitting groove into which the shroud is fitted, and the slide groove is formed at the bottom of the stationary blade side fitting groove. It is characterized by being.

  In the gas turbine seal structure according to a fifth aspect of the present invention, the transition piece seal has an insertion groove extending from an outer surface toward the slide groove, and the drop prevention means is inserted into the insertion groove and the It penetrates the first seal plate.

  In the gas turbine seal structure according to a sixth aspect of the present invention, the transition piece seal has an insertion groove extending from an outer surface toward the slide groove, and the drop prevention means is inserted into the insertion groove and the The first seal plate is in contact with the end face of the stationary blade side.

  In the gas turbine seal structure according to a seventh aspect of the present invention, the drop-off prevention means is provided in the opening on the stationary blade side of the slide groove and abuts on the end surface on the stationary blade side of the first seal plate. It is a resin member that can prevent the movement of the first seal plate.

  In the gas turbine seal structure according to an eighth aspect of the present invention, the transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and the first seal plate moves relative to each other. It consists of a plurality of divided plates that can be expanded and contracted in the circumferential direction of the tail tube seal, and is fitted into the pair of recesses in an extended state, and the drop-off prevention means holds the extended state of the first seal plate. And

  In the gas turbine seal structure according to the ninth aspect of the present invention, the transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and the first seal plate is in the pair of recesses. Thus, it can be elastically deformed in the circumferential direction of the transition piece seal, and also serves as the drop-off preventing means by elastically deforming.

  According to the gas turbine seal structure according to the first aspect of the present invention, a plurality of combustors are disposed in the circumferential direction of the turbine, and fuel is supplied to the compressed air and burned by the plurality of combustors. In a gas turbine that obtains rotational power by supplying to a stationary blade and a moving blade of a turbine, it comprises a divided portion that is divided into a plurality of portions in the circumferential direction while connecting a tail cylinder of a plurality of combustors and a shroud of a stationary blade The first seal plate that connects the transition piece seal, the transition piece seal that is assembled to the transition piece or the shroud adjacent to each other, and the first seal plate is removed from the transition piece seal. And preventable drop-off prevention means.

  Therefore, rotational power can be obtained by supplying fuel to compressed air by a plurality of combustors provided in the circumferential direction of the turbine and burning it, and supplying the generated combustion gas to the stationary blades and moving blades of the turbine. The tail cylinder seals divided into a plurality of division parts in the circumferential direction are connected to the tail cylinders of the plurality of combustors and the shrouds of the stationary blades. Since the first seal plate is connected by the first seal plate and the first seal plate is prevented from falling off the tail tube seal by the drop-off preventing means, the tail tube seal can be properly attached. Leakage of air from the gap of the tail tube seal into the tail tube can be reliably suppressed.

  According to the gas turbine seal structure of the second aspect of the present invention, at least one pair of the adjacent divided portions has a pair of slide grooves that allow the first seal plate to move along the flow direction of the combustion gas. The drop prevention means is fixed to the tail tube seal and abuts against the first seal plate to prevent the movement of the first seal plate. Therefore, a pair of slide grooves are formed in the adjacent divided portions, and the adjacent divided portions are connected by inserting the first seal plate into the pair of slide grooves, and then the first seal plate is Since it is prevented from falling off the tail cylinder seal by abutting against the drop prevention means fixed to the tail cylinder seal, the combustor tail cylinder and the stationary blade shroud can be reliably connected, Assembling of the shroud of the stationary blade to the tail tube of the combustor can be facilitated.

  According to the seal structure of the gas turbine according to the invention of claim 3, the transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and is fitted into the pair of recesses before the tail tube seal is assembled. A second seal plate is provided to be fixed, and the first seal plate can be fitted into the pair of slide grooves after the tail tube seal is assembled. Therefore, the seal plate that connects the divided portions of the transition piece seal has two types, that is, the first seal plate and the second seal plate, and the second seal plate is connected to the transition piece or shroud of the transition piece seal. Before assembling, the divided portions are connected by being fitted and fixed in a pair of concave portions formed on opposing surfaces of the adjacent divided portions, and the first seal plate is the tail tube or shroud of the tail tube seal. After the assembly, the split parts are connected to each other by being movably inserted into the pair of slide grooves, and the drop prevention means prevents the drop off. Therefore, when assembling a plurality of adjacent split parts, first, The adjacent divided portions are connected by the two seal plates, and after the tail tube seal is assembled to the tail tube or the shroud, the last pair of divided portions are connected by the first seal plate. Since the dropping of the first sealing plate is prevented by the falling-off preventing means can be reliably installed seal plate assembled to the end, the last pair of split portions can be reliably connected.

  According to the seal structure of the gas turbine according to the fourth aspect of the present invention, the transition piece seal has the stationary blade side fitting groove into which the shroud is fitted, and the slide groove is formed at the bottom of the stationary blade side fitting groove. . Accordingly, since the slide groove is provided in communication with the stationary blade side fitting groove at the bottom of the stationary blade side fitting groove into which the shroud is fitted, the slide groove can be easily formed, and the shroud can slide. By fitting in the stationary blade side fitting groove adjacent to the groove, it is possible to assist in preventing the first seal plate from falling off by the drop-off preventing means, and thus more reliably preventing the first seal plate from dropping off. Can do.

  According to the gas turbine seal structure of the fifth aspect of the present invention, the transition piece seal has the insertion groove extending from the outer surface toward the slide groove, and the drop prevention means is inserted into the insertion groove and the first Pass through the seal plate. Accordingly, the drop-off prevention means is inserted into the insertion groove extending from the outer surface of the tail tube seal toward the slide groove and penetrates the first seal plate, so that the drop-off prevention means is fixed to the tail tube seal and the first The movement of the first seal plate in the slide groove through the one seal plate can be restricted, and the first seal plate can be reliably prevented from falling off the tail tube seal.

  According to the seal structure of the gas turbine according to the sixth aspect of the present invention, the transition piece seal has the insertion groove extending from the outer surface toward the slide groove, and the drop prevention means is inserted into the insertion groove and the first Abuts against the end face of the seal plate on the stationary blade side. Accordingly, the drop-off prevention means is inserted into the insertion groove extending from the outer surface of the transition piece seal toward the slide groove and comes into contact with the end face on the stationary blade side of the first seal plate, so that the drop-off prevention means is fixed to the transition piece seal. In addition, the movement of the first seal plate within the slide groove can be restricted, and the first seal plate can be reliably prevented from falling off the tail tube seal. Furthermore, since it is not necessary to process the first seal plate, the manufacturing efficiency can be improved.

  According to the gas turbine seal structure according to the seventh aspect of the present invention, the drop-off prevention means is provided in the opening on the stationary blade side of the slide groove and abuts against the end surface of the first seal plate on the stationary blade side. This is a resin member that can prevent the seal plate from moving. Accordingly, the drop-off preventing means constituted by a resin member is filled in the opening on the stationary blade side of the slide groove and abuts on the end surface of the sealing plate on the stationary blade side, so that the movement of the first seal plate within the slide groove is prevented. Therefore, it is possible to reliably prevent the first seal plate from falling off the tail tube seal. Furthermore, since it is not necessary to form a groove other than the slide groove in the tail tube seal in order to prevent the first seal plate from falling off, the manufacturing efficiency can be improved.

  According to the gas turbine seal structure of the invention according to claim 8, the tail tube seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and the first seal plate moves relative to each other by the relative movement. It consists of a plurality of divided plates that can be expanded and contracted in the circumferential direction of the cylinder seal, and is fitted into the pair of recesses in the extended state, and the drop-off prevention means holds the extended state of the first seal plate. Therefore, the first seal plate is fitted into a pair of recesses formed on the opposing surfaces of the adjacent split portions, and the plurality of split plates move relative to each other and expand and contract in the circumferential direction of the tail tube seal. In addition, the divided parts to be assembled at the end can be reliably connected to each other, and further, since the extended state is maintained by the drop-off preventing means, it is possible to prevent the first seal plate from dropping from the tail tube seal. . Furthermore, the complicated shape of the transition piece seal is not required, and all the divided portions can be formed in the same shape, so that the manufacturing efficiency can be improved.

  According to the gas turbine seal structure of the ninth aspect of the present invention, the transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions, and the first seal plate has a tail in the pair of recesses. The cylinder seal can be elastically deformed in the circumferential direction and also serves as a drop-off preventing means by being elastically deformed. Accordingly, the first seal plate is provided in a pair of recesses formed on the opposing surfaces of the adjacent divided portions after being reduced and elastically deformed, and extends in the circumferential direction of the tail tube seal within the pair of recesses. Therefore, the divided parts assembled last can be reliably connected to each other, and further, elastically deformed to extend in the concave part and come into contact with the inner surface of the concave part. It is possible to prevent the one seal plate from falling off the tail tube seal. Furthermore, the complicated shape of the transition piece seal is not required, and all the divided portions can be formed in the same shape, and it is not necessary to process the first seal plate, thereby improving the manufacturing efficiency. Can do.

  Embodiments of a gas turbine seal structure according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same.

  1 is a cross-sectional view taken along a direction orthogonal to the circumferential direction of the tail tube seal of the gas turbine according to the first embodiment of the present invention, and FIG. 2 is a cross-sectional view of the tail tube seal of the gas turbine according to the first embodiment of the present invention. FIG. 3 is a partial side view along the circumferential direction, FIG. 3 is a side view of an end face of the split portion of the gas turbine according to the first embodiment of the present invention, and FIG. 4 is a seal plate of the gas turbine according to the first embodiment of the present invention. FIG. 5 is a schematic configuration diagram of the gas turbine according to the first embodiment of the present invention, and FIG. 6 is a cross-sectional view showing the combustor of the gas turbine according to the first embodiment of the present invention.

  As shown in FIG. 5, in the gas turbine 1 of the first embodiment having the seal structure according to the present invention, a plurality of combustors 12 are arranged in the circumferential direction of the turbine 13, and fuel is supplied to the compressed air by the plurality of combustors 12. Is supplied and burned, and the generated combustion gas is supplied to the stationary blade 21 and the moving blade 22 of the turbine to obtain rotational power.

  The gas turbine 1 includes a compressor 11, a combustor 12, a turbine 13, and an exhaust chamber 14, and a generator (not shown) is connected to the turbine 13 via a rotor (turbine shaft) 24. The compressor 11 has an air intake port 15 for taking in air, a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16, and a bleed manifold 19 is provided on the outside thereof. ing. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner. In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20. The exhaust chamber 14 has an exhaust diffuser 23 that is continuous with the turbine 13. Further, the rotor 24 is positioned so as to pass through the central portion of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14, and the end portion on the compressor 11 side is rotatably supported by the bearing portion 25. On the other hand, the end portion on the exhaust chamber 14 side is rotatably supported by the bearing portion 26. A plurality of disk plates are fixed to the rotor 24, the rotor blades 18 and 22 are connected to each other, and a drive shaft of a generator (not shown) is connected to an end portion on the compressor 11 side.

  Therefore, the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature and high-pressure compressed air. Combustion occurs when a predetermined fuel is supplied to the compressed air. The high-temperature and high-pressure combustion gas that is the working fluid generated in the combustor 12 passes through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. While the generator connected to 24 is driven, the exhaust gas is discharged into the atmosphere after the dynamic pressure is converted to static pressure by the exhaust diffuser 23 in the exhaust chamber 14.

  More specifically, the above-described combustor 12 is disposed behind the outlet portion of the compressor 11 and in front of the inlet portion of the turbine 13 as shown in FIG. A plurality of the combustors 12 are annularly arranged along the circumferential direction of the turbine 13, that is, along the circumferential direction of the plurality of stationary blades 21 assembled in an annular shape. Each combustor 12 includes an inner cylinder 31, a tail cylinder 32, and a fuel nozzle 33.

  The inner cylinder 31 is a cylindrical member that constitutes a combustion chamber of the combustor 12, and is fixed to the compressor casing 16 of the compressor 11. The fuel nozzle 33 is a nozzle for injecting fuel into the combustion chamber, and is inserted into the inner cylinder 31 and arranged. Specifically, the fuel nozzle 33 is disposed from an inlet portion 31a as one end portion in the axial direction of the inner cylinder 31, and includes a pilot nozzle 33a and a main nozzle 33b.

  The tail cylinder 32 is formed in a cylindrical shape, and has an outlet 31b as the other end in the axial direction of the inner cylinder 31 (the end opposite to the end on the side where the fuel nozzle 33 is provided). The outlet 31b of the inner cylinder 31 and the first stage stationary blade 21 of the turbine 13 are connected. The transition piece 32 is curved with a cross-sectional area becoming smaller from an inlet portion 32a as an end portion on the inner tube 31 side toward an outlet portion 32b as an end portion on the stationary blade 21 side. In the transition piece 32, the inlet portion 32 a having a large cross-sectional area is the upstream side of the flow of air sent from the compressor 11 as described above, and the outlet portion is curved while the cross-sectional area is reduced. 32b is the downstream side. Further, a tail tube seal 50 is provided at the outlet portion 32 b of the tail tube 32.

  The stationary blade 21 of the turbine 13 described above is configured by connecting an outer shroud 41 and an inner shroud 42 to each end portion in the longitudinal direction of the blade portion 40, and a plurality of stationary blades 21 are assembled in an annular shape. In the state, it is supported by the turbine casing 20 (see FIG. 5).

  The transition piece seal 50 includes an outer transition piece seal 51 that connects the outer wall surface of the plurality of transition pieces 32 and the outer shroud 41 of the stationary blade 21, and an inner side that connects the inner wall surface of the plurality of transition pieces 32 and the inner shroud 42. A tail tube seal 52 is provided. The outer transition piece seal 51 and the inner transition piece seal 52 are both formed in an annular shape along the circumferential direction of the plurality of stationary blades 21 assembled in an annular shape.

  In this gas turbine 1, the air (compressed air) compressed by the compressor 11 passes through the space outside the tail cylinder 32 and the inner cylinder 31, cools the tail cylinder 32 and the inner cylinder 31, and then the inner cylinder 31. Is supplied into the combustor 12 through the inlet portion 31a. In the inner cylinder 31 and the tail cylinder 32 as combustion chambers of the combustor 12, the air-fuel mixture of the compressed air and the fuel injected from the fuel nozzle 33 burns and becomes high-temperature and high-pressure combustion gas. Then, this combustion gas is supplied to the stationary blade 21 of the turbine 13 through the transition piece 32 and the transition piece seal 50.

  By the way, as shown in FIG. 2, the outer transition pipe seal 51 and the inner transition pipe seal 52 of the transition pipe seal 50 are formed in an annular shape by a divided portion 53 that is divided into a plurality in the circumferential direction. This avoids stress concentration due to thermal expansion and vibration of the tail cylinder 32 of the combustor 12, the outer shroud 41 of the stationary blade 21, the inner shroud 42, and the like. However, as described above, compressed air from the compressor 11 is supplied to the combustor 12. This compressed air is once sent to the space around the combustor 12 including the inner cylinder 31 and the tail cylinder 32. Then, the inner cylinder 31 and the tail cylinder 32 are cooled, and then supplied into the inner cylinder 31 from the inlet portion 31a (see FIG. 6). Therefore, the compressed air outside the tail cylinder 32 flows into the tail cylinder 32 through the gap between the divided tail cylinder seals 50, and the gas turbine is operated due to a decrease in the temperature of the combustion gas or wasteful consumption of air that is not involved in combustion. May reduce efficiency.

  Therefore, in the gas turbine 1 of the present embodiment, as shown in FIGS. 1 and 2, it is possible to prevent the seal plate 60 that connects the adjacent divided portions 53 and the seal plate 60 from falling off the tail tube seal 50. By providing a drop prevention pin 70 as a drop prevention means, air leakage into the tail cylinder 32 through a gap between the tail cylinder 32 of the combustor 12 and the outer shroud 41 and inner shroud 42 of the stationary blade 21 is suppressed. I am trying. In the following description, the seal structure in the outer tail cylinder seal 51 that mainly connects the transition piece 32 and the outer shroud 41 will be described. However, in the inner transition piece seal 52 that connects the transition piece 32 and the inner shroud 42. Since the seal structure is almost the same as this, the description thereof is omitted.

  As shown in FIG. 1, flanges 32c and 32d are formed so that the tail cylinder 32 protrudes outwardly on the outer surface of the outlet portion 32b (surface opposite to the combustion gas flow path indicated by the arrow in the figure). . The flange 32c is formed at the opening end portion of the outlet portion 32b, and the flange 32d is formed with a slight gap from the flange 32c, whereby a groove portion 32e is formed between the flange 32c and the flange 32d.

  Each of the divided portions 53 of the outer tail cylinder seal 51 includes a tail cylinder side locking portion 54 having a U-shaped cross-sectional shape opened in the center side of the tail cylinder 32, and a static cross section along the flow direction of the combustion gas. It has a stationary blade side locking portion 55 having a U-shape that is open on the outer shroud 41 side of the blade 21. The stationary blade side locking portion 55 is formed so as to extend from one end of the transition piece side locking portion 54 to the stationary blade 21 side, and the stationary blade side locking portion 55 and the transition piece side locking portion 54 are integrally formed. As a result, each divided portion 53 of the outer tail tube seal 51 is formed. The transition piece side locking portion 54 is formed so that the U-shaped opening faces the tail cylinder 32 side, and forms the transition piece side fitting groove 54b in the hollow portion of the U shape. And the front-end | tip part 54a which is the other end part of the transition piece side latching | locking part 54 is inserted in the above-mentioned groove part 32e, and the flange 32c is inserted in the transition piece side fitting groove 54b, and is pin-fixed. The flange 32c and the flange 32d of the cylinder 32 are engaged with the transition piece side locking portion 54 of the divided portion 53, whereby each divided portion 53 of the outer tail tube seal 51 is attached to the outlet portion 32b of the tail tube 32. It becomes possible.

  On the other hand, the stationary blade side engaging portion 55 of each divided portion 53 of the outer tail pipe seal 51 is formed so that the U-shaped opening faces the outer shroud 41 side, and the stationary blade side fitting groove is formed in the U-shaped hollow portion. 55b is formed. That is, the stationary blade side fitting groove 55 b is formed on the end surface opposite to the transition piece side locking portion 54. Further, the stationary blade side fitting groove 55b is formed substantially parallel to the flow direction of the combustion gas, that is, substantially parallel to the outer shroud 41. By inserting the outer shroud 41 of the stationary blade 21 into the stationary blade side fitting groove 55 b, the tail cylinder 32 and the outer shroud 41 of the stationary blade 21 can be connected by the divided portions 53 of the outer tail cylinder seal 51.

  In addition, as shown in FIG. 2, each divided portion 53 of the outer tail tube seal 51 has a protruding portion 53 a and a depressed portion 53 b on the inner peripheral side of the end surface facing the adjacent divided portion 53. The protruding portion 53a protrudes in the circumferential direction toward the end face of the adjacent divided portion 53, and the depressed portion 53b is formed to be depressed in the circumferential direction corresponding to the protruding portion 53a of the adjacent divided portion 53. As a result, the protruding portion 53a and the depressed portion 53b are arranged in such a manner that the distance between the end faces facing the divided portion 53 is minimized while the adjacent divided portions 53 are connected by the seal plate 60 described later. Compressed air can be prevented from flowing into the transition piece 32 from the inside.

  Here, as shown in FIG. 1, a pair of adjacent divided portions 53 of the outer tail cylinder seal 51 has a pair of slide grooves 56 that allow the seal plate 60 to move along the flow direction of the combustion gas. The slide groove 56 is formed in the bottom portion 55a of the above-described stationary blade side fitting groove 55b so as to communicate with the stationary blade side fitting groove 55b. Further, the slide groove 56 also opens at the opposing end surfaces of the pair of divided portions 53 where the slide groove 56 is formed, and the openings face each other to form a pair of slide grooves 56. Thereby, the seal plate 60 can move in the pair of slide grooves 56, and therefore, the seal plate 60 can be fitted in the pair of slide grooves 56. The seal plate 60 is formed in a rectangular plate shape.

  On the other hand, as shown in FIG. 3, the remaining divided portions 53 in which the slide groove 56 is not formed have a pair of concave portions 57 on the end surfaces facing the adjacent divided portions 53. In addition, the recessed part 57 is similarly formed in the end surface in which the opening of this slide groove 56 of the pair of division part 53 in which the slide groove 56 is formed is not formed. The concave portion 57 is opposed to the concave portion 57 of the adjacent divided portion 53 to form a space in which one seal plate 60 is fitted.

  That is, the seal plate 60 is fitted and fixed to the first seal plate 61 movably fitted in the pair of slide grooves 56 as shown in FIG. 1 and the pair of recesses 57 as shown in FIG. There are two types of second seal plate 62. Further, the second seal plate 62 is fitted and fixed in the pair of recesses 57 before the outer tail cylinder seal 51 is assembled to the tail cylinder 32, while the first seal plate 61 is fixed to the outer tail cylinder seal 51. Is inserted into the pair of slide grooves 56 so as to be movable. In other words, the first seal plate 61 is inserted into the pair of slide grooves 56 of the adjacent divided portion 53 of the outer tail cylinder seal 51 already assembled to the tail cylinder 32 to connect the two. Moreover, since the division part 53 in which a pair of slide groove | channel 56 is formed is only one pair in a present Example as above-mentioned, it is the 1st among several seal plates 60 which each connect the some division | segmentation part 53. There is only one seal plate 61, and the rest is the second seal plate 62.

  In this way, a pair of slide grooves 56 is formed in the adjacent divided portions 53, the first seal plate 61 fitted into the pair of slide grooves 56 is one, and the rest is the second seal plate 62. Thus, the second seal plate 62 is fitted into and fixed to a pair of concave portions 57 formed on the opposing surfaces of the adjacent divided portions 53, thereby connecting the divided portions 53, and the first seal plate 61. Is inserted in the slide groove 56 by moving in the flow direction of the combustion gas in the pair of slide grooves 56, and connects the divided portions 53. When the adjacent divided portions 53 are assembled to form the annular outer tail cylinder seal 51, first, the adjacent divided portions 53 are connected by the second seal plate 62, and this outer tail tube seal 51 is connected. After the first seal plate 61 is assembled to the tail cylinder 32, only the last pair of divided portions 53 are connected by moving the first seal plate 61 within the slide groove 56, so that the first seal plate 61 to be assembled last is attached to the outer tail. The cylinder seal 51 can be reliably mounted, and the outer tail cylinder seal 51 can be mounted at an appropriate position. Note that the seal plate 60 formed in a rectangular plate shape connects the divided portions 53 such that the wide surface faces the radial direction of the outer tail tube seal 51. That is, the seal plate 60 is provided so as to cover the gaps between the divided portions 53.

  Further, as shown in FIG. 1, the first seal plate 61 to be assembled last is prevented from dropping by a drop-off preventing pin 70 as a drop-off preventing means. Specifically, the two divided portions 53 in which the pair of slide grooves 56 of the divided portions 53 of the outer tail pipe seal 51 are formed have one insertion groove 58 extending from the outer surface toward the slide groove 56 one by one. Have. As shown in FIG. 4, each insertion groove 58 is a circular groove in which an opening formed on the outer surface of the dividing portion 53 has a circular shape, and extends to a position that penetrates the slide groove 56. The drop-off prevention pin 70 is formed in a cylindrical shape, is inserted into each insertion groove 58 and penetrates the first seal plate 61. The drop-off prevention pin 70 is fixed to the dividing portion 53 and abuts against the first seal plate 61 to restrict the movement of the first seal plate 61 in the slide groove 56. That is, after the last pair of divided portions 53 are connected by the first seal plate 61, the first seal plate 61 is prevented from falling off by the dropout prevention pin 70. It should be noted that the outer tail cylinder seal 51 is preferably arranged so that the first seal plate 61 to be assembled last is positioned on the upper side in the vertical direction. Thereby, the drop-off prevention pin 70 and the first seal plate 61 can be more reliably prevented from falling off.

  The outer shroud 41 and the inner shroud 42 of the stationary blade 21 described above are arranged such that after the last first seal plate 61 is attached to the outer tail cylinder seal 51 and the inner tail cylinder seal 52, The tail tube seal 52 is assembled. Here, as described above, the slide groove 56 is formed at the bottom 55a of the stationary blade side fitting groove 55b so as to communicate with the stationary blade side fitting groove 55b, so that the outer shroud 41 and the inner shroud 42 slide. By fitting in the stationary blade side fitting groove 55b adjacent to the groove 56, the outer shroud 41 and the inner shroud 42 themselves also assist in preventing the first seal plate 61 from falling off.

  As described above, the outer tail pipe seal 51 and the inner shroud 42 including the plurality of divided portions 53 are formed in an annular shape by connecting the adjacent divided portions 53 by the first seal plate 61 and the second seal plate 62. In addition, as shown in FIG. 2, the seal plate 60 covers the circumferential gaps between the divided portions 53, so that the flow area of the compressed air flowing from the outside to the inside of the tail cylinder 32 is reduced. Inflow of air into the cylinder 32 is suppressed.

  According to the gas turbine 1 according to the first embodiment of the present invention described above, the plurality of combustors 12 are arranged in the circumferential direction of the turbine 13, and the plurality of combustors 12 supply fuel to the compressed air for combustion. In the gas turbine that obtains rotational power by supplying the generated combustion gas to the stationary blade 21 and the moving blade 22 of the turbine 13, the tail cylinder 32 of the plurality of combustors 12, the outer shroud 41 of the stationary blade 21, and the inner shroud. 42, and a transition piece seal 50 (outer transition piece seal 51, inner transition piece seal 52) composed of a divided portion 53 divided into a plurality of portions in the circumferential direction, and a transition piece seal 50 assembled to the transition piece 32. A first seal plate 61 that couples the first seal plate 61 by inserting it into the adjacent divided portion 53 and a drop-off prevention pin 70 that can prevent the first seal plate 61 from falling off the tail tube seal 50 are provided.

  Accordingly, fuel is supplied to the compressed air and combusted by a plurality of combustors 12 provided in the circumferential direction of the turbine 13, and the generated combustion gas is supplied to the stationary blades 21 and the moving blades 22 of the turbine 13 to obtain rotational power. During this time, the transition piece 32 of the plurality of combustors 12 and the stationary blades 21 are separated by the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) that is divided into a plurality of division parts 53 in the circumferential direction. The outer shroud 41 and the inner shroud 42 are connected, assembled to the tail cylinder 32, and each of the divided portions 53 adjacent to each other in the circumferential direction are connected by the first seal plate 61. Since the seal plate 61 is prevented from falling off from the transition piece seal 50, the transition piece seal 50 can be properly mounted. As a result, the first seal is provided. Since the rate 61 reliably covers the gap between the divided portions 53, the flow area of the compressed air flowing from the outside to the inside of the tail cylinder 32 is reduced, and the air from the gap of the tail cylinder seal 50 into the tail cylinder 32 is reduced. Can be reliably suppressed.

  Furthermore, according to the gas turbine 1 which concerns on Example 1 of this invention demonstrated above, at least one pair of the adjacent division parts 53 can move the 1st seal plate 61 along the flow direction of combustion gas. The drop prevention pin 70 is fixed to the tail cylinder seal 50 (the outer tail cylinder seal 51 and the inner tail cylinder seal 52) and is in contact with the first seal plate 61. The movement of the first seal plate 61 can be prevented. Accordingly, a pair of slide grooves 56 are formed in the adjacent divided portions 53, and the adjacent divided portions 53 are connected by inserting the first seal plate 61 into the pair of slide grooves 56, and then the first Since the seal plate 61 is prevented from falling off the tail cylinder seal 50 by abutting against the drop prevention pin 70 fixed to the tail cylinder seal 50, the outer side of the tail cylinder 32 and the stationary blade 21 of the combustor 12. The shroud 41 and the inner shroud 42 can be reliably connected, and the outer shroud 41 and the inner shroud 42 of the stationary blade 21 can be easily assembled to the tail cylinder 32 of the combustor 12.

  Furthermore, according to the gas turbine 1 according to the first embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) is provided on the opposing surface of the adjacent divided portion 53. A second seal plate 62 that has a pair of recesses 57 and is fitted into and fixed to the pair of recesses 57 before the tail tube seal 50 is assembled is provided. It can be fitted into the pair of slide grooves 56 after assembly. Therefore, there are two types of seal plates 60 that connect the split portions 53 of the transition piece seal 50, the first seal plate 61 and the second seal plate 62, and the second seal plate 62 corresponds to the transition piece seal 50. Before assembling to the transition piece 32, the divided portions 53 are connected by being fitted into and fixed to a pair of concave portions 57 formed on opposing surfaces of the adjacent divided portions 53, and the first seal plate 61 is connected. After the assembly of the transition piece seal 50 to the transition piece 32, the divided portion 53 is connected by being movably inserted into a pair of slide grooves, and the fall prevention pin 70 prevents the fall off, so that a plurality of adjacent When assembling the divided parts 53, first, the adjacent divided parts 53 are connected by the second seal plate 62, and after the tail cylinder seal 50 is assembled to the tail cylinder 32, the last pair of parts 53 are separated. Since the first seal plate 61 is connected by the first seal plate 61, and the first seal plate 61 is prevented from falling off by the drop-off preventing pin 70, the seal plate 60 to be assembled last can be surely installed. The pair of divided portions 53 can be reliably connected.

  Further, according to the gas turbine 1 according to the first embodiment of the present invention described above, the outer shroud 41 and the inner shroud 42 are fitted to the tail cylinder seal 50 (the outer tail cylinder seal 51 and the inner tail cylinder seal 52). And the slide groove 56 is formed on the bottom 55a of the stationary blade side fitting groove 55b. Accordingly, since the slide groove 56 is provided in communication with the stationary blade side fitting groove 55b at the bottom 55a of the stationary blade side fitting groove 55b into which the outer shroud 41 and the inner shroud 42 are fitted, the slide groove 56 can be easily formed. Further, the outer shroud 41 and the inner shroud 42 are fitted into the stationary blade side fitting groove 55 b adjacent to the slide groove 56, thereby preventing the first seal plate 61 from being dropped by the drop prevention pins 70. Since it can assist, the drop-off of the first seal plate 61 can be prevented more reliably.

  Furthermore, according to the gas turbine 1 according to the first embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) is inserted from the outer surface toward the slide groove 56. The drop prevention pin 70 having the groove 58 is inserted into the insertion groove 58 and penetrates the first seal plate 61. Accordingly, the drop-off prevention pin 70 is inserted into the insertion groove 58 extending from the outer surface of the transition piece seal 50 toward the slide groove 56 and passes through the first seal plate 61. And the movement of the first seal plate 61 in the slide groove 56 through the first seal plate 61 can be restricted, and the first seal plate 61 falls off the tail tube seal 50. This can be surely prevented.

  FIG. 7 is a cross-sectional view taken along a direction orthogonal to the circumferential direction of the transition seal of the gas turbine according to the second embodiment of the present invention, and FIG. 8 is a front view of the seal plate of the gas turbine according to the second embodiment of the present invention. FIG. The gas turbine 201 according to the second embodiment has substantially the same configuration as the gas turbine 1 according to the first embodiment, but is different from the gas turbine 1 according to the first embodiment in that the tail tube seal does not have an insertion groove. Different. In addition, about the structure, effect | action, and effect which are common in Example 1, while overlapping description is abbreviate | omitted as much as possible, the same code | symbol is attached | subjected.

  As shown in FIG. 7, in the gas turbine 201 of the present embodiment, a resin member 270 made of resin as a drop-off prevention unit is used instead of the drop-off prevention pin 70 as the drop-off prevention unit of the first embodiment. The resin member 270 is provided in the opening on the stationary blade 21 side of the slide groove 56 and can contact the end surface 62a of the first seal plate 61 on the stationary blade 21 side to prevent the movement of the first seal plate 61. And As shown in FIG. 8, the resin member 270 is provided at one place in each of a pair of adjacent divided portions 53 in which a pair of slide grooves 56 are formed. The resin member 270 is formed of a hard resin member as described above, so that the stationary blade 21 of the slide groove 56 can be formed without providing the insertion groove 58 as in the first embodiment in the divided portion 53 of the tail cylinder seal 50. It is possible to directly fill and fix the side opening.

  According to the gas turbine 201 according to the second embodiment of the present invention described above, the resin member 270 as the drop-off preventing means is provided in the opening on the stationary blade 21 side of the slide groove 56 and the first seal plate 61 is provided. It is a resin member that can prevent the movement of the first seal plate 61 by contacting the end face 62a on the stationary blade 21 side. Accordingly, the resin member 270 formed of a resin member is provided in the opening on the stationary blade 21 side of the slide groove 56 and abuts on the end surface 62a of the first seal plate 61 on the stationary blade 21 side. The movement of the first seal plate 61 inside can be restricted, and the first seal plate 61 falls off from the divided portion 53 of the tail tube seal 50 (the outer tail tube seal 51 and the inner tail tube seal 52). Can be reliably prevented. Furthermore, since it is not necessary to form a groove other than the slide groove 56 in the divided portion 53 in order to prevent the first seal plate 61 from falling off, the manufacturing efficiency can be improved.

  FIG. 9 is a cross-sectional view taken along a direction orthogonal to the circumferential direction of the transition seal of the gas turbine according to the third embodiment of the present invention, and FIG. 10 is a front view of the seal plate of the gas turbine according to the third embodiment of the present invention. FIG. The gas turbine 301 according to the third embodiment has substantially the same configuration as that of the gas turbine 1 according to the first embodiment, but differs from the gas turbine 1 according to the first embodiment in that the drop-off prevention means does not penetrate the seal plate. In addition, about the structure, effect | action, and effect which are common in Example 1, while overlapping description is abbreviate | omitted as much as possible, the same code | symbol is attached | subjected.

  As shown in FIG. 9, in the gas turbine 301 of the present embodiment, the insertion grooves 358 are respectively provided on the opening side on the stationary blade 21 side of the slide groove 56 in the pair of divided portions 53. As shown in FIG. 10, each insertion groove 358 is a circular groove in which an opening formed on the outer surface of the dividing portion 53 has a circular shape, and extends to the inner surface of the slide groove 56. A drop prevention pin 370 as a drop prevention means is inserted into each insertion groove 358 and abuts against the end face 62a on the stationary blade 21 side of the first seal plate 61 to prevent the movement of the first seal plate 61. Make it possible.

  According to the gas turbine 301 according to the third embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) is inserted into the insertion groove 358 extending from the outer surface toward the slide groove 56. The drop prevention pin 370 is inserted into the insertion groove 358 and abuts against the end face 62a of the first seal plate 61 on the stationary blade 21 side. Accordingly, the drop prevention pin 370 is inserted into the insertion groove 358 extending from the outer surface of the transition piece seal 50 toward the slide groove 56 and comes into contact with the end surface 62a of the first seal plate 61 on the stationary blade 21 side. The pin 370 is fixed to the dividing portion 53 of the transition piece seal 50 and can restrict the movement of the first seal plate 61 in the slide groove 56. It can be reliably prevented from falling off from the dividing portion 53. Furthermore, since it is not necessary to process the first seal plate 61 such as a through hole, the manufacturing efficiency can be improved.

  FIG. 11 is a front view of the seal plate of the gas turbine according to the fourth embodiment of the present invention. The gas turbine 401 according to the fourth embodiment has substantially the same configuration as that of the gas turbine 301 according to the third embodiment, but is different from the gas turbine 301 according to the third embodiment in that drop-off prevention means is formed in a plate shape. . In addition, about the structure, effect | action, and effect which are common in Example 3, while overlapping description is abbreviate | omitted as much as possible, the same code | symbol is attached | subjected.

  As shown in FIG. 11, in the gas turbine 401 according to the present embodiment, the insertion grooves 458 are respectively provided on the opening side on the stationary blade 21 side of the slide groove 56 in the pair of divided portions 53. Each insertion groove 458 is a rectangular groove in which an opening formed on the outer surface of the dividing portion 53 forms a rectangular shape, and extends to the inner surface of the slide groove 56. The drop-off prevention plate 470 as a drop-off prevention means is formed in a rectangular plate shape, is inserted so as to span the two insertion grooves 458, and is formed on the end surface 62 a of the first seal plate 61 on the stationary blade 21 side. The movement of the first seal plate 61 can be prevented by contacting the entire surface.

  According to the gas turbine 401 according to the fourth embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) is inserted into the insertion groove 458 extending from the outer surface toward the slide groove 56. A drop-off prevention plate 470 having a plate shape is inserted into each insertion groove 458 and abuts against the end surface 62a of the first seal plate 61 on the stationary blade 21 side. Therefore, the drop-off prevention plate 470 is inserted so as to span the insertion grooves 458 extending from the outer surface of the transition piece seal 50 toward the slide groove 56, and the end surface 62a of the first seal plate 61 on the stationary blade 21 side is inserted. Since it comes into contact with the entire surface, the drop-off prevention plate 470 is fixed to the divided portion 53 of the transition piece seal 50 and can restrict the movement of the first seal plate 61 in the slide groove 56. It is possible to reliably prevent the seal plate 61 from dropping from the divided portion 53 of the transition piece seal 50. Furthermore, since it is not necessary to process the first seal plate 61 such as a through hole, the manufacturing efficiency can be improved. Further, since the drop-off prevention plate 470 contacts the entire surface of the end surface 62a, sufficient reliability can be ensured as compared with the case where the drop-off prevention pin 370 prevents the drop-off as in the third embodiment, for example. .

  FIG. 12 is a plan view of a seal plate of a gas turbine according to a fifth embodiment of the present invention, FIG. 13 is a cross-sectional view taken along line AA of the seal plate of the gas turbine according to the fifth embodiment of the present invention, and FIG. It is a fragmentary sectional view along the circumferential direction of the transition piece seal of the gas turbine which concerns on Example 5 of invention. The gas turbine 501 according to the fifth embodiment has substantially the same configuration as the gas turbine 1 according to the first embodiment, but is different from the gas turbine 1 according to the first embodiment in that the tail tube seal does not have a slide groove. Different. In addition, about the structure, effect | action, and effect which are common in Example 1, while overlapping description is abbreviate | omitted as much as possible, the same code | symbol is attached | subjected.

  As shown in FIG. 12, in the gas turbine 501 of the present embodiment, the first seal plate 561 includes a first plate 561a and a second plate 561b as a plurality of relatively movable divided plates. As shown in FIG. 13, the first plate 561a has a U-shaped cross-sectional shape perpendicular to the direction in which the first plate 561 can move relative to the first plate 561a. It has a part 561c. The second plate 561b is formed in a shape in which a cross-sectional shape in a direction perpendicular to the relatively movable direction is formed in a rectangular shape, and a part of both sides of the rectangular shape protrudes as an engaging portion 561d. The second plate 561b is disposed in a U-shaped hollow portion of the first plate 561a so that the engaging portion 561c and the engaging portion 561d are engaged with each other. The first plate 561a and the second plate 561b have a rail structure when the engaging portion 561c and the engaging portion 561d are engaged with each other, and can be relatively moved along the engaging portion 561c and the engaging portion 561d. It becomes. In addition, through holes 561e are formed in the first plate 561a and the second plate 561b, respectively.

  As shown in FIG. 14, the transition piece seal 50 has a pair of concave portions 557 on the opposing surfaces of the adjacent divided portions 53. The concave portion 557 is the same as the concave portion 57 of the first embodiment, and forms a space in which a pair of first seal plates 561 are fitted by facing the concave portion 557 of the adjacent divided portion 53. The first seal plate 561 is provided in the pair of recesses 557 so that the direction of relative movement coincides with the circumferential direction of the transition piece seal 50. Accordingly, the first seal plate 561 can be expanded and contracted in the circumferential direction of the tail tube seal 50 by the relative movement of the first plate 561a and the second plate 561b within the pair of recesses 557. The first seal plate 561 extends in the circumferential direction of the tail tube seal 50 by moving in the direction in which the first plate 561a and the second plate 561b are separated from each other in the pair of recesses 557. In the extended state, the pair of recesses 557 are fitted to each other, and the adjacent divided portions 53 are connected.

  The first seal plate 561 is prevented from dropping from the split portion 53 of the tail tube seal 50 by being held in an extended state by a drop prevention pin 570 as a drop prevention means. This drop-off prevention pin 570 is inserted into two insertion grooves 558 extending from the outer surface of the tail tube seal 50 toward the recess 557 in the same manner as the drop-off prevention pin 70 of the first embodiment, and the first plate 561a and the second plate Each penetrates through the through hole 561e of 561b. Thereby, the relative movement of the first plate 561a and the second plate 561b in the extended first seal plate 561 is restricted, and the dropout is prevented.

  In the gas turbine 501 of this embodiment, the transition piece seal 50 does not include the slide groove 56 of the first embodiment. That is, in this embodiment, there is no seal plate that is movably fitted in the pair of slide grooves 56, and all the seal plates are fitted and fixed in the pair of recesses 557. However, from the viewpoint of assembling the transition piece seal 50 composed of the plurality of divided portions 53, only the seal plate to be assembled last is changed to the first seal plate 561 composed of the first plate 561a and the second plate 561b as described above. Then, since all the seal plates can be properly assembled, the other seal plates may be ordinary plate-like seal plates. Then, the drop prevention pin 570 only needs to prevent the drop of only the first seal plate 561 assembled last.

  According to the gas turbine 501 according to the fifth embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) has a pair of surfaces on the opposing surfaces of the adjacent divided portions 53. The first seal plate 561 has a concave portion 557, and includes a first plate 561a and a second plate 561b as a plurality of divided plates that can expand and contract in the circumferential direction of the tail tube seal 50 by relative movement and is in an extended state. And the drop prevention pin 570 holds the first seal plate 561 in the extended state. Accordingly, the first seal plate 561 is fitted into a pair of recesses 557 formed on the opposing surfaces of the adjacent divided portions 53, and the first plate 561a and the second plate 561b move relative to each other in the recesses 557. Since it extends and contracts in the circumferential direction of the transition piece seal 50, the divided parts 53 to be assembled at the end can be reliably connected to each other, and further, the extended state is held by the drop-off preventing pin 570, so that the first seal plate 561 Can be prevented from falling off the tail tube seal 50. Furthermore, the complicated shape of the transition piece seal 50 is not required, and all the divided portions 53 can be formed in the same shape, so that the manufacturing efficiency can be improved.

  FIG. 15 is a partial cross-sectional view along the circumferential direction of the transition piece seal of the gas turbine according to the sixth embodiment of the present invention. The gas turbine 601 according to the sixth embodiment has substantially the same configuration as the gas turbine 501 according to the fifth embodiment, but differs from the gas turbine 501 according to the fifth embodiment in that the seal plate can be elastically deformed. In addition, about the structure, effect | action, and effect which are common in Example 5, while overlapping description is abbreviate | omitted as much as possible, the same code | symbol is attached | subjected.

  As shown in FIG. 15, in the gas turbine 601 of the present embodiment, the transition piece seal 50 has a pair of recesses 657 on the opposing surfaces of the adjacent divided portions 53. The first seal plate 661 is configured to be elastically deformable in the circumferential direction of the transition piece seal 50 within the pair of recesses 657, that is, the first seal plate 661 itself forms a flexible structure. As the first seal plate 661, for example, a flexible metal cloth seal obtained by combining wire-like metals in a cloth-like layer can be used.

  After the first seal plate 661 is installed on one side of the pair of recesses 657, the divided parts 53 to be assembled last are aligned from both sides, and the first seal plate 661 is pushed into the pair of recesses 657. Are assembled into a pair of recesses 657 by being elastically deformed. Then, after being accommodated in the pair of recesses 657, the adjacent split portions 53 are connected by extending so as to return to the original shape in the recesses 657 and elastically deformed as described above. The seal plate 661 itself also serves as a dropping prevention means.

  According to the gas turbine 601 according to the sixth embodiment of the present invention described above, the transition piece seal 50 (the outer transition piece seal 51 and the inner transition piece seal 52) has a pair of surfaces on the opposing surfaces of the adjacent divided portions 53. The first seal plate 661 has a recess 657 and can be elastically deformed in the circumferential direction of the tail tube seal 50 in the pair of recesses 657 and also serves as a drop-off preventing means by being elastically deformed. Therefore, the first seal plate 661 is provided in a pair of recesses 657 formed on the opposing surfaces of the adjacent divided portions 53 after being reduced and elastically deformed, and the tail cylinder seal 50 is provided in the pair of recesses 657. Since the divided parts 53 to be assembled at the end can be securely connected to each other and further elastically deformed, the parts are extended in the concave part 657 and come into contact with the inner surface in the concave part 657. The first seal plate 661 itself can prevent the first seal plate 661 from dropping from the tail tube seal 50. Further, the complicated shape of the tail tube seal is not required, and all the divided portions can be formed in the same shape, and the manufacturing efficiency can be improved because it is not necessary to process the seal plate.

  In addition, the sealing structure of the gas turbine which concerns on the Example of this invention mentioned above is not limited to the Example mentioned above, A various change is possible in the range described in the claim. In the above description, the slide groove 56 has been described as being provided at the bottom 55a of the stationary blade side fitting groove 55b so as to communicate with the stationary blade side fitting groove 55b, but is not limited thereto.

  In the above description, since the slide groove 56 is formed at the bottom 55a of the stationary blade side fitting groove 55b so as to communicate with the stationary blade side fitting groove 55b, the outer shroud 41 and the inner shroud 42 are formed as slide grooves. 56, the outer shroud 41 and the inner shroud 42 themselves have been described as assisting in preventing the first seal plate 61 from falling off by being fitted in the stationary blade side fitting groove 55b adjacent to the outer shroud 56. If only the shroud 42 can sufficiently prevent the first seal plate 61 from falling off, only the outer shroud 41 and the inner shroud 42 are used as the dropping prevention means, and the fall prevention pins 70 and 370, the resin member 270 and the drop prevention plate 470 are used. It is not necessary to provide other drop-off prevention means.

  In the above description, the drop-off prevention pins 70, 370, and 570 have been described as being formed in a cylindrical shape, but may be in a prismatic shape or a plate shape. In the above description, the first seal plate 61 movably fitted in the pair of slide grooves 56 has been described as being only one, but a plurality of the first seal plates 61 may be provided. That is, a pair of slide grooves 56 may be formed in a plurality of sets of divided portions 53. Further, a recess is provided in the inner part of the slide groove 56 and the tip of the first seal plate 61 is formed so as to protrude in a wedge shape. The wedge shape of the tip of the first seal plate 61 is formed in the recess in the slide groove 56. The first seal plate 61 may be prevented from falling off by engaging this part. In this case, the wedge-shaped portion serves as a drop-off preventing means.

  The gas turbine seal structure according to the present invention reliably suppresses the leakage of air into the transition piece through the gap between the transition piece of the combustor and the shroud of the stationary blade. It can be applied as a cylinder seal structure.

It is sectional drawing along the direction orthogonal to the circumferential direction of the tail pipe seal of the gas turbine which concerns on Example 1 of this invention. It is a partial side view along the circumferential direction of the transition piece seal of the gas turbine which concerns on Example 1 of this invention. It is a side view which sees the end surface of the division part of the gas turbine which concerns on Example 1 of this invention. It is a front view of the seal plate of the gas turbine which concerns on Example 1 of this invention. It is a schematic block diagram of the gas turbine which concerns on Example 1 of this invention. It is sectional drawing which shows the combustor of the gas turbine which concerns on Example 1 of this invention. It is sectional drawing along the direction orthogonal to the circumferential direction of the transition piece seal of the gas turbine which concerns on Example 2 of this invention. It is a front view of the seal plate of the gas turbine which concerns on Example 2 of this invention. It is sectional drawing along the direction orthogonal to the circumferential direction of the tail-cylinder seal of the gas turbine which concerns on Example 3 of this invention. It is a front view of the seal plate of the gas turbine which concerns on Example 3 of this invention. It is a front view of the seal plate of the gas turbine which concerns on Example 4 of this invention. It is a top view of the seal plate of the gas turbine which concerns on Example 5 of this invention. It is AA sectional drawing of the seal plate of the gas turbine which concerns on Example 5 of this invention. It is a fragmentary sectional view along the circumferential direction of the transition piece seal of the gas turbine concerning Example 5 of the present invention. It is a fragmentary sectional view along the circumferential direction of the transition piece seal of the gas turbine concerning Example 6 of the present invention.

Explanation of symbols

1, 201, 301, 401, 501, 601 Gas turbine 11 Compressor 12 Combustor 13 Turbine 17, 21 Stator blade 18, 22 Rotor blade 31 Inner cylinder 32 Tail cylinder 33 Fuel nozzle 40 Blade section 41 Outer shroud 42 Inner shroud 50 Tail tube seal 51 Outer tail tube seal 52 Inner tail tube seal 53 Divided portion 55a Bottom portion 55b Stator blade side fitting groove 56 Slide groove 57 Recess 58, 358, 458, 558 Insert groove 60 Seal plates 61, 561, 661 First seal Plate 62 Second seal plate 62a End face 70, 370, 570 Drop-off prevention pin (drop-off prevention means)
270 Resin member 470 Fall-off prevention plate (fall-off prevention means)
557, 657 Concave portion 561a First plate (divided plate)
561b Second plate (split plate)
570 Fall-off prevention pin (fall-off prevention means)

Claims (9)

A plurality of combustors are arranged in the circumferential direction of the turbine, and the plurality of combustors supply fuel to the compressed air for combustion, and the generated combustion gas is supplied to the turbine stationary blades and moving blades to generate rotational power. In the resulting gas turbine,
A transition piece seal comprising a plurality of divided portions divided in a circumferential direction while connecting the plurality of combustor transition pieces and the stationary blade shroud;
A first seal plate that couples both by inserting into the divided portion adjacent to the transition piece seal assembled to the transition piece or the shroud;
A drop prevention means capable of preventing the first seal plate from falling off the tail pipe seal,
Gas turbine seal structure. At least a pair of the adjacent divided portions has a pair of slide grooves that allow the first seal plate to move along the flow direction of the combustion gas,
The drop-off prevention means is fixed to the tail tube seal and is capable of preventing the movement of the first seal plate by contacting the first seal plate.
The gas turbine seal structure according to claim 1. The transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions,
A second seal plate is provided to be fitted and fixed in the pair of recesses before the tail tube seal is assembled;
The first seal plate can be fitted into the pair of slide grooves after the tail tube seal is assembled.
The gas turbine seal structure according to claim 2. The transition piece seal has a stationary blade side fitting groove into which the shroud is fitted,
The slide groove is formed at the bottom of the stationary blade side fitting groove,
A seal structure for a gas turbine according to claim 2 or claim 3. The transition piece seal has an insertion groove extending from the outer surface toward the slide groove,
The drop-off prevention means is inserted into the insertion groove and penetrates the first seal plate.
The gas turbine seal structure according to any one of claims 2 to 4. The transition piece seal has an insertion groove extending from the outer surface toward the slide groove,
The drop-off prevention means is inserted into the insertion groove and abuts against an end surface of the first seal plate on the stationary blade side.
The gas turbine seal structure according to any one of claims 2 to 4. The drop-off prevention means is a resin that is provided in the opening on the stationary blade side of the slide groove and that prevents the movement of the first seal plate by coming into contact with the end surface on the stationary blade side of the first seal plate. It is a member made of,
The gas turbine seal structure according to any one of claims 2 to 4. The transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions,
The first seal plate is composed of a plurality of divided plates that can expand and contract in the circumferential direction of the transition piece seal by relative movement, and is fitted into the pair of recesses in an extended state.
The drop-off prevention means holds the extended state of the first seal plate,
The gas turbine seal structure according to claim 1. The transition piece seal has a pair of recesses on the opposing surfaces of the adjacent divided portions,
The first seal plate is elastically deformable in the circumferential direction of the tail tube seal in the pair of recesses and also serves as the drop-off preventing means by elastically deforming.
The gas turbine seal structure according to claim 1.

Images