JP4235208B2 - Gas turbine tail tube structure - Google Patents

Description

  The present invention relates to a transition structure of a gas turbine in which a plurality of transition cylinders that guide high-temperature and high-pressure combustion gas from a combustor to a turbine are covered with a cooling cover.

  The transition piece of the gas turbine is a flow path for guiding the high-temperature and high-pressure combustion gas from the combustor to the turbine and has a high temperature, and therefore needs to be effectively cooled. As the cooling structure of the transition piece, as shown in FIG. 11, a full cover type cooling cover 81 that can cover almost the entire portion from the upstream end 80 a to the downstream end 80 b of the transition piece 80 is used. By providing the entire surface with a required gap, and introducing compressed air A from the compressor through a number of impingement cooling holes 81a provided in the cooling cover 81 to collide with the outer peripheral surface of the tail cylinder 80. In addition, one that impinges the tail cylinder 80 is known (see Patent Document 1).

  As another cooling structure for the transition piece, a half-cover type cooling cover having a length L that is approximately half of the upstream side of the cooling cover 81 in FIG. 11 is provided from the upstream end of the transition piece to the middle portion. Provided with a required gap with respect to the outer peripheral surface of the upstream portion of the compressor, and the compressed air A from the compressor is introduced into the gap between the cooling cover and the tail tube from the downstream end of the cooling cover to convectively cool. In addition, there is also known one that performs impingement cooling using a number of impingement cooling holes provided in the cooling cover. In this cooling structure, in addition to the above configuration, the inner surface on the downstream side of the transition piece that is not covered by the cooling cover is formed by compressed air that is ejected into the interior of the transition piece from a large number of small-diameter air introduction holes formed in this portion. The film is cooled by the air film.

Japanese Patent Publication No. 5-24337

  However, in the cooling structure using the full cover type cooling cover 81, the entire outer peripheral surface of the tail tube 80 can be impingement cooled by the cooling cover 81, so that the metal temperature distribution of the tail tube 80 is substantially uniform over the entire surface. On the other hand, as shown in FIG. 8, for each of the plurality of tail cylinders 80, the downstream-side fan-shaped gas outlets are arranged on the circumference corresponding to the first stage turbine nozzle of the turbine. When arranging the downstream ends of the cooling covers 81, the downstream ends of the cooling covers 81 do not interfere with each other so that the downstream ends of the cooling covers exist around the outlets of the downstream ends of the tail cylinders 80. It is necessary to provide and arrange a gap C1 that can absorb the expansion and avoid mutual interference. As this gap C1 is provided, each of the adjacent tail cylinders 80 is arranged. Interval C2 in the upstream end outlet becomes larger.

  Therefore, from the space corresponding to the relatively large gap C2 existing between each adjacent tail cylinder 80, the combustion gas does not flow through the downstream end outlet of the tail cylinder 80 and flow into the turbine as it is. As shown in FIG. 10, the temperature and flow velocity of the combustion gas at the inlet of the first stage turbine nozzle both have non-uniform circumferential distributions that decrease at locations corresponding to the above-described gap C2. If the distribution of the combustion gas temperature and flow velocity in the circumferential direction is not uniform, the turbine efficiency is lowered, the engine performance is lowered, and the heat resistance life of the nozzle pieces arranged in the circumferential direction forming the first stage turbine nozzle is reduced. Variation occurs.

  On the other hand, in the cooling structure using the half cover type cooling cover, since there is no cooling cover near the downstream end outlet of the tail tube, as shown in FIG. Can be disposed close to each other with a small gap C3 that can absorb the thermal expansion due to the combustion gas, so that the temperature and flow velocity of the combustion gas at the inlet of the first stage turbine nozzle are both substantially uniform in the circumferential direction. There is an advantage of distribution. However, in this cooling structure, since almost half of the downstream side of the transition piece is not covered with the cooling cover, the transition piece cannot be cooled effectively, so the metal temperature of the transition piece tends to be high, The heat resistant life of the tail tube cannot be secured sufficiently. Therefore, it is not suitable for a gas turbine of a type where the temperature of the combustion gas is high.

  When adopting a cooling structure using a half cover type cooling cover for a gas turbine of a type having a high combustion gas temperature, as described above, a small diameter for film cooling is provided in the entire area of the downstream half of the tail tube. This is possible by forming a large number of air introduction holes. However, this cooling structure using film cooling not only increases the manufacturing cost, but also the compressed air introduced into the tail cylinder from a large number of air introduction holes mixes with the combustion gas and lowers the temperature of the combustion gas. In order for the combustion gas of the required temperature to flow into the turbine, it is necessary to set the temperature of the combustion gas in the combustor to a higher temperature that allows for a temperature drop due to film cooling. As a result, the combustor and the transition piece following it tend not only to have a shorter life as the thermal load increases, but also to increase the NOx value as the temperature of the combustion gas increases.

  Therefore, the present invention can maintain the temperature and flow velocity of the combustion gas in a uniform circumferential distribution so that the combustion gas can flow into the turbine. An object of the present invention is to provide a tail tube structure of a gas turbine that can sufficiently ensure the life of a turbine nozzle and further suppress an increase in NOx value.

In order to achieve the above object, a transition structure of a gas turbine according to the present invention includes a plurality of transition tubes arranged in a circumferential direction for introducing combustion gas from a combustor into a turbine, and a downstream end portion of the transition tube. Sealing materials for sealing between the first stage turbine nozzles of the turbine are respectively fixed to the outer diameter side and the inner diameter side of the turbine, and downstream ends of the cooling cover in the vicinity of the downstream end of the tail tube A notch that is recessed from the edge toward the upstream side is formed, the circumferential position of the outer surface of each side at the downstream end of the cooling cover , and the circumferential direction of the sealing material on the outer diameter side and inner diameter side The position of the end portion substantially coincides with the circumferential position of the outer surface of each side portion at the downstream end portion of the tail tube exposed by the notch, and the downstream end portion of each tail tube is adjacent to the adjacent tail tube. The thermal expansion due to combustion gas with respect to the downstream end of Only through the corresponding circumferential gap, they are arranged close to.

  According to this configuration, even when the cooling cover has a full cover type shape that can cover almost the entire outer peripheral surface of the transition piece, the notches are provided on both sides of the downstream end of the cooling cover. As a result, there is no cooling cover on both sides in the circumferential direction at the downstream end of the transition piece, so the downstream ends of the transition pieces are close to each other without interfering with each other. Therefore, the gas outlets of the tail pipes can be arranged close to each other with a small gap that can absorb the thermal expansion due to the combustion gas. Thereby, since both the temperature and flow velocity of the combustion gas at the inlet of the first stage turbine nozzle can be made to have a substantially uniform circumferential distribution, high turbine efficiency can be obtained. In addition, since compressed air can be introduced into the gap between the transition piece and the cooling cover to cool almost the entire transition piece, there is no need to provide air introduction holes for film cooling in the transition piece. The heat resistance life of the vessel, the transition piece and the first stage turbine nozzle can be sufficiently secured, and an increase in the NOx value can be suppressed.

In addition, since the downstream ends of the adjacent tail cylinders can be brought as close as possible without the downstream ends of the cooling covers interfering with each other, the temperature and flow velocity at the inlet of the first stage turbine nozzle are effectively reduced. Uniform in the circumferential direction.

  In the present invention, preferably, the cooling cover is provided with a plurality of cooling holes for introducing impingement cooling by introducing the compressed air and causing it to collide with the outer peripheral surface of the tail tube. According to this configuration, the tail cylinder can be effectively cooled by impingement cooling with compressed air introduced from a large number of cooling holes provided in the cooling cover that covers substantially the entire outer peripheral surface of the tail cylinder.

  According to the transition structure of the gas turbine of the present invention, by providing the notches on both sides of the downstream end of the cooling cover, the cooling cover is equivalent to the full cover type that can cover almost the entire transition piece. Even though it is shaped, the downstream ends of the plurality of transition pieces can be arranged close to each other with a required small gap, so that the temperature and flow velocity of the combustion gas at the inlet of the first stage turbine nozzle can both have a uniform circumferential distribution. As a result, the turbine efficiency can be kept high. Furthermore, it is possible to effectively cool the entire transition of the transition piece while suppressing costs, and to sufficiently ensure the lives of the combustor, transition piece and first stage turbine nozzle, and to suppress an increase in the NOx value.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. FIG. 1 is a partially cutaway side view showing a gas turbine using a transition piece structure according to an embodiment of the present invention. In the figure, a gas turbine 1 compresses air 1A by a compressor 2 and guides the compressed air A to a combustor 3, and injects gas or liquid fuel F into the combustor 3 for combustion, and the high temperature thereof. By introducing the high-pressure combustion gas G to the turbine 4 through the tail cylinder 26, the turbine 4 is driven by the energy of the combustion gas G. The turbine 4 drives the compressor 2 and also drives a load such as a generator (not shown).

  In this embodiment, the gas turbine 1 provided with the axial flow compressor as the said compressor 2 is illustrated. This axial flow compressor 2 includes an intake duct by a combination of a large number of moving blades 13 disposed on the outer periphery of the rotating shaft 12 and stationary blades 15 disposed in a plurality of stages on the inner peripheral surface of the compressor housing 14. The air 1A sucked from 16 is compressed. A main housing 60 is connected to the downstream side of the compressor housing 14, and the compressed air A from the compressor 2 is supplied to an annular high-pressure air chamber 17 formed in the main housing 60.

  A plurality of combustors 3 (eight in this embodiment) are arranged in the annular high-pressure air chamber 17 along the circumferential direction at equal intervals, and the compressed air A supplied to the high-pressure air chamber 17 is disposed. Is introduced into the combustion chamber 22 inside the combustion cylinder 21 as indicated by arrows a and b. On the other hand, the fuel F is injected into the combustion chamber 22 from the fuel nozzle 23 of the combustor 3 and mixed with the compressed air A and combusted. It flows into the turbine 4 through the transition piece 26 connected to the downstream side in the flow direction.

  FIG. 2 is an enlarged vertical sectional view of a portion of the tail tube structure in FIG. The tail cylinder 26 has an upstream end portion 26 a connected to the combustion cylinder 21 of the combustor 3 and a downstream end portion 26 b connected to the first stage turbine nozzle 18 of the turbine 4. The tail cylinder 26 is covered with a cooling cover 7 with a required gap 27 almost entirely on the outer peripheral surface, and the gap 27 is fed from the outlet of the diffuser 24 of the compressor 2 to the high-pressure air chamber 17. The supplied compressed air A is ejected from a large number of cooling holes of the cooling cover 7 described later, and the ejected high-speed air flow collides with the outer peripheral surface of the tail cylinder 26 to impinge cool the tail cylinder 26. Details of the impingement cooling will be described later. The compressed air A introduced into the gap 27 flows toward the upstream side of the combustor 3 through the gap 27 and is then introduced into the combustion chamber 22 inside the combustion cylinder 21.

  Each tail tube 26 is an integrally formed product made of metal, and as shown in FIG. 4 which is a plan view of the tail tube 26 and the cooling cover 7, the opening of the upstream end portion 26a is the combustion tube 21 (FIG. 2). ), And the gas outlet, which is the opening of the downstream end portion 26b, is an annular first-stage turville nozzle, as shown in FIG. 6 which is a perspective view of the transition piece 26 and the cooling cover 7. 18 is formed in a sector shape obtained by dividing a ring corresponding to 18 into a plurality of divisions (in this embodiment, eight divisions).

  On the other hand, as clearly shown in FIG. 2, the cooling cover 7 has an upstream end 7 a at the substantially same position as the upstream end 26 a of the tail cylinder 26 in the flow direction of the combustion gas G, and a downstream end 7 b of the tail cover 26. 26 is located slightly upstream from the downstream end portion 26b, and has the same shape as the full cover type that can cover almost the entire outer surface of the tail tube 26 except for a part of the downstream end portion 26b. Yes. As clearly shown in FIG. 5 that is a bottom view, the cooling cover 7 has a shape that is recessed toward the upstream side from the downstream end edge 7bb on both sides of the downstream end portion 7b that covers the vicinity of the downstream end portion 26b of the tail tube 26. A notch 8 is formed. The notch 8 has a maximum circumferential width W1 of the downstream end 7b of the cooling cover 7 substantially equal to a maximum circumferential width W2 of the downstream end 26b of the tail tube 26 exposed by the notch 8. The shape is set. In other words, the cutout portion 8 is formed in a shape that is cut out and excluded only from a portion of the cooling cover 7 that protrudes outward in the circumferential direction from the downstream end portion 26 b of the tail tube 26.

  As shown in FIG. 2, the upstream end portion 26 a of the tail cylinder 26 is fitted with the downstream end portion of the combustion cylinder 21 inside a connecting cylinder portion 28 that is slightly enlarged in diameter and formed in a large diameter. Thus, it is connected to the combustion cylinder 21. On the other hand, the downstream end portion 26b of the transition piece 26 is connected to the first stage turbine nozzle (static blade) 18 of the turbine 4 by a connection structure described below.

  That is, as shown in FIG. 6, an arc-shaped outer seal material 10 is provided at the downstream end portion 26b of the tail tube 26 on the outer diameter side (upper side in the figure) of the gas outlet 26e that opens in a fan shape. Arc-shaped inner seal materials 11 are fixed to the inner diameter side (lower side in the figure) of each of them with a structure to be described later. In addition, a connecting flange portion 9 that is located on the downstream side of the downstream end portion 7 b of the cooling cover 7 is integrally projected on the outer surface of the tail tube 26.

  A single pin insertion hole 19 is formed in the central portion of the connection flange portion 9 in the circumferential direction, and screw insertion holes 20 are formed at both sides of the pin insertion hole 19. Further, the outer seal material 10 is integrally formed with two first bosses 30, 30 projecting to the outer diameter side of the gas turbine and one second boss 32 positioned between them. Similarly, two first bosses 31, 31 projecting to the inner diameter side of the gas turbine and one second boss 33 positioned therebetween are integrally formed. The first bosses 30 and 31 are provided with screw holes 34 and 37, and the second bosses 32 and 33 are provided with pin insertion holes 38 and 39. Further, the tail tube 26 is integrally formed with mounting bosses 41 and 42 which have the same shape with respect to the two first bosses 30 and 31 of the outer seal material 10 and the inner seal material 11 and are overlapped with each other. In addition, a positioning boss 40 having the same shape as that of the second boss 33 of the inner seal material 11 and overlapping each other is integrally formed.

  As shown in FIG. 3, which is an enlarged view of the portion III in FIG. 2, the outer seal material 10 and the inner seal material 11 are inserted into the outer diameter side and the inner diameter side of the downstream end portion 26 b of the tail tube 26, respectively. When the positioning pins 29 and 47 attached to the connecting flange portion 9 of the tail tube 26 and the positioning boss 40 are inserted into the holes 38 and 39, the two bolts 44 are respectively positioned in a state of being positioned with respect to the tail tube 26. , 45 are screwed into the screw holes 34, 37 of the first bosses 30, 31 via the screw insertion holes (not shown) of the mounting bosses 41, 42 of the tail cylinder 26 shown in FIG. Thus, the downstream end portion 26b of the tail tube 26 is fixed to the outer diameter side and the inner diameter side. Thus, the outer seal material 10 and the inner seal material 11 are fixed to the tail cylinder 26 in an accurate positioning state that does not protrude in the circumferential direction with respect to the downstream end portion 26b of the tail cylinder 26.

  Further, as shown in FIG. 3, the positioning pin 48 protruding from the turbine nozzle support member 43 is inserted into the pin insertion hole 19 of the connecting flange portion 9 of the tail cylinder 26, and the bolt 49 is a screw of the connecting flange portion 9. The connecting flange portion 9 is fixed to the turbine nozzle support member 43 by being screwed into a screw hole (not shown) of the turbine nozzle support member 43 through the insertion hole 20 (FIG. 6), and the downstream end portion 26 b of the tail tube 26. Is supported by the turbine nozzle support member 43 via the connecting flange portion 9. The turbine nozzle support member 43 is supported by the main housing 60 of FIG. In this state, the upstream end of the first stage turbine nozzle 18 of the turbine 4 is fitted into the outer seal material 10 and the inner seal material 11, so that the space between the first stage turbine nozzle 18 and the tail cylinder 26 is hermetically sealed.

  On the other hand, as shown in FIG. 4, the cooling cover 7 is formed by combining two cover halves 7A and 7B divided into left and right parts. As shown in FIG. 5, the upstream end portion 7a of the cooling cover 7 has a pair of connecting pieces projecting outward at both upper and lower end portions in the circumferential direction of the upstream ends of the cover halves 7A and 7B. When the bolts 52 are screwed into the screw holes of the other connecting piece 50 through the insertion holes of the one connecting piece 51 in a state where the 50 and 51 are overlapped, the upstream ends of the cover halves 7A and 7B are The outer diameter side and the inner diameter side are connected to each other. In addition, the intermediate portion of the cooling cover 7 is formed by superimposing one connecting piece 53, 54 projecting outward from each end on the outer diameter side of the intermediate portion of each cover half body 7A, 7B. In this state, the cover 57 and the nut 58 are screwed together so that the intermediate portions of the cover halves 7A and 7B are connected to each other. The connection structure of the cover halves 7A and 7B at the downstream end 7b of the cooling cover 7 will be described later.

  As shown in FIG. 2, the flow sleeve 62 of the cooling cover 7 is a cylindrical body having a flange at the upstream end, the flange is supported by the main housing 60 by the bolt 61, and the downstream end is upstream of the cooling cover 7. The upstream end portion 7 a of the cooling cover 7 is supported by being fitted inside an opening recess 59 formed by expanding the inner peripheral surface of the end portion 7 a in the vicinity of the opening. The upstream end 7 a is supported by the main housing 60 via the flow sleeve 62. Further, in the opening recess 59 of the cooling cover 7, the tips of the four positioning pins 63 that are integrally projected at equal intervals of 90 ° from the outer surface of the upstream end portion of the transition piece 26 toward the outer diameter side. Is touching lightly. Thus, the upstream end portion 26 a of the tail tube 26 is positioned at a relative position that maintains a predetermined gap 27 with respect to the cooling cover 7.

  The downstream end portion 7 b of the cooling cover 7 extends to a location in the vicinity of the connecting flange portion 9 of the tail cylinder 26, and forms a small gap 64 with the connecting flange portion 9. Two mounting block pieces 68 projecting from the outer diameter side and the inner diameter side of the tail cylinder 26 are inserted into two insertion holes 67 provided on the outer diameter side and the inner diameter side near the downstream end of the cooling cover 7. Are respectively inserted. On the other hand, as shown in FIG. 4, connecting block pieces 69, 69 projecting in the vicinity of the insertion holes 67 at the outer diameter side ends of the cover halves 7 A, 7 B of the cooling cover 7 are the mounting block pieces 68. Are overlapped with each other so as to be sandwiched from both sides, and these are screwed together by bolts 70 and nuts 71. Further, as shown in the bottom view of FIG. 5, the connecting block pieces 69, 69 projecting in the vicinity of the insertion hole 67 are also provided on the inner diameter side ends of both cover halves 7 </ b> A, 7 </ b> B of the cooling cover 7. The mounting block pieces 68 are overlapped with each other so as to be sandwiched from both sides, and these are screwed together by bolts 70 and nuts 71. Thereby, the downstream end 7 b of the cooling cover 7 is supported by the tail tube 26.

  As shown in FIGS. 4 to 6, the cooling cover 7 is formed with a large number of cooling holes 72 almost entirely. The compressed air A in the high-pressure air chamber 17 in FIG. 2 is introduced into the cooling cover 7 through these cooling holes 72 and collides with the outer peripheral surface of the tail tube 26, whereby the tail tube 26 is impinged.

  As shown in FIG. 7, in this embodiment, the gas turbine 1 having eight tail cylinders 26 is illustrated, and the gas outlet 26e at the downstream end portion 26b of the tail cylinder 26 corresponds to approximately 1/8 circumference. It is formed into a fan shape. These tail cylinders 26 are arranged in an annular shape corresponding to the annular inlet openings of the first stage turbine nozzle 18 (FIG. 2) by arranging the gas outlets 26e of the respective downstream end portions 26b in the circumferential direction.

  The cooling cover 7 shown in FIG. 6 has the same shape as a full cover type that can cover almost the entire outer surface of the transition piece 26 except the connecting flange portion 9 at the downstream end. A pair of left and right cutout portions 8 are formed on both sides of the downstream end portion 26b and recessed from the downstream end edge 7bb toward the upstream side. The cutout portions 8 are formed on the left and right sides of the cooling cover 7. The circumferential position P1 of the end (in this case, the upper edge of the notch 8) is set to a shape that substantially matches the circumferential position P2 of the both ends of the tail tube 26 exposed by the notch 8. In this way, the area that can cover the tail tube 26 in the cooling cover 7 is made as large as possible while avoiding interference in which the downstream end portions 7b of the two adjacent cooling covers 7 contact each other.

  Accordingly, as clearly shown in FIG. 7, each tail tube 26 allows the gas outlets 26 e of the respective downstream end portions 26 b as much as possible without considering the interference between the respective downstream end portions of the respective cooling covers 7. Since each gas outlet 26e of each tail tube 26 can be made close to each other, the gap C3 that can absorb the thermal expansion due to the combustion gas G, that is, a half-cover type cooling cover (FIG. 9), They can be arranged annularly in an arrangement close to each other, leaving an equivalent gap C3. Therefore, in this tail tube structure, the temperature and flow velocity of the combustion gas G at the inlet of the first stage turbine nozzle 18 of FIG. 3 are both more uniform in the circumferential distribution as indicated by the two-dot chain lines TT and VV in FIG. can do. Thereby, while the fall of the efficiency of the turbine 4 can be suppressed, the dispersion | variation in the heat-resistant lifetime of each nozzle piece located in the circumferential direction which forms the first stage turbine nozzle 18 is suppressed, and the life of the first stage turbine nozzle 18 can be lengthened.

  Further, in the transition piece structure, the compressed air A introduced into the gap 27 shown in FIG. 2 from a number of cooling holes 72 provided in the cooling cover 7 covering almost the entire outer peripheral surface of the transition piece 26 shown in FIG. By impinging on the outer surface of the tail tube 26 and performing impingement cooling, the outer peripheral surface of the tail tube 26 can be effectively cooled. The portion exposed by the two notches 8 on both sides of the tail tube 26 is convectively cooled by the compressed air A flowing from the outlet of the diffuser 24 of the compressor 2 toward the high-pressure air chamber 17 as indicated by arrows. Is done. In other words, this tail tube structure effectively cools the entire outer peripheral surface of the tail tube 26 without providing a costly cooling structure such as film cooling in the tail tube 26, thereby extending the life of the tail tube 26. Enough can be secured. Furthermore, since the air inlet hole for film cooling is not provided in the tail cylinder 26, it is possible to suppress an increase in manufacturing cost, and the air for film cooling is mixed into the combustion gas so that the combustion gas temperature at the inlet of the first stage turbine nozzle is reduced. Since it does not decrease, it is not necessary to set the temperature of the combustion gas in the combustor to a high level. Thereby, since the thermal load of the combustor and the subsequent transition piece does not increase, the life of the combustor and the transition piece can be extended, and further the increase in the NOx value can be suppressed.

  In addition, instead of providing a large number of cooling holes 72 in the cooling cover 7 and performing impingement cooling, cooling in which the tail cylinder 26 is convectively cooled by introducing compressed air A into the gap 27 between the tail cylinder 26 and the cooling cover 7. Even if the structure is adopted, since the cooling cover 7 covers almost the whole of the tail tube 26, substantially the whole of the tail tube 26 can be effectively cooled in the same manner as the above-described embodiment in which the tail tube 26 is impinged. Can do.

It is a partially broken side view showing a gas turbine using a tail tube structure according to an embodiment of the present invention. FIG. 2 is an enlarged longitudinal sectional view of a portion of a tail tube structure in FIG. 1. FIG. 3 is an enlarged view of part III in FIG. 2. It is a top view which shows the transition piece and cooling cover in a gas turbine same as the above. FIG. 5 is a bottom view of FIG. 4. It is a perspective view which shows the transition piece and cooling cover same as the above. It is the figure which looked at the arrangement | sequence state of the gas outlet 26e of each downstream end when a plurality of above-mentioned tail pipes were combined from the downstream side. It is the figure of the part which looked at the arrangement state of the gas outlet of each downstream end of each of a plurality of transition pipes from the downstream side at the time of using the conventional full cover type cooling cover. It is the figure of the part which looked at the arrangement state of the gas outlet of the downstream end of each of a plurality of transition pipes at the time of using the conventional half cover type cooling cover from the downstream side. It is a figure which shows the circumferential direction distribution of the temperature and flow velocity of the combustion gas of the turbine inlet_port | entrance part of the gas turbine using the structure of FIG. It is sectional drawing of a part of gas turbine using the conventional full cover type cooling cover.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Compressor 3 Combustor 4 Turbine 7 Cooling cover 7b Downstream end portion of cooling cover 7bb Downstream end edge 8 Notch portion 26 Tail tube 26b Downstream end portion of tail tube 72 Cooling hole G Combustion gas A Compressed air P1, P2 circumferential position

Claims (2)

A plurality of circumferentially arranged tail cylinders for introducing combustion gas from the combustor into the turbine;
A cooling cover that covers the outer periphery of the transition piece and introduces compressed air from the compressor between the transition piece and the transition piece;
A sealing material for sealing between the first stage turbine nozzle of the turbine is fixed to the outer diameter side and the inner diameter side of the downstream end portion of the tail cylinder,
Notches that are recessed from the downstream edge toward the upstream side are formed on both sides of the cooling cover in the vicinity of the downstream end of the tail tube,
The circumferential position of the outer surface of each side at the downstream end of the cooling cover , and the position of the circumferential end of the sealing material on the outer diameter side and the inner diameter side are exposed at the downstream end of the tail tube. Almost matches the circumferential position of the outer surface of each side of the part,
The tail end of the gas turbine in which the downstream end portion of each transition piece is disposed close to the downstream end portion of the adjacent transition piece only through a circumferential gap corresponding to the thermal expansion due to the combustion gas. Tube structure.   2. The gas turbine tail cylinder structure according to claim 1, wherein a plurality of cooling holes are formed in the cooling cover to introduce impingement cooling by introducing the compressed air into the cooling cover and causing it to collide with the outer peripheral surface of the tail cylinder.

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