JP2023166152A - Combustor tube, combustor, and gas turbine - Google Patents

Abstract

To reduce the flow rate of a cooling medium while keeping the durability of a combustor tube even if a secondary fuel nozzle is attached to the combustor tube.SOLUTION: A combustor tube in which fuel can be combusted on an inner peripheral side comprises: a plurality of cooling passages formed between an inner peripheral surface and an outer peripheral surface, and through which a cooling medium can flow; a nozzle attachment through-hole penetrating from the outer peripheral surface to the inner peripheral surface; and a bypass passage formed in an annular shape along an edge of the nozzle attachment through-hole around the nozzle attachment through-hole, and through which the cooling medium can flow. A plurality of first cooling passages out of the plurality of cooling passages communicate with the bypass passage at their respective outlets. A plurality of second cooling passages out of the plurality of cooling passages communicate with the bypass passage at their respective inlets.SELECTED DRAWING: Figure 4

Description

The present disclosure relates to a combustor tube capable of burning fuel on the inner peripheral side, a combustor having this combustor tube, and a gas turbine including this combustor.

A gas turbine includes a compressor that compresses air, a combustor that burns fuel with the air compressed by the compressor to generate combustion gas, and a turbine that is driven by the combustion gas from the combustor. .

The combustor has a combustor tube (combustion tube or transition tube) in which fuel is burned. The inner circumferential surface of this combustor cylinder is exposed to high temperature combustion gas, and thus becomes extremely high temperature. Therefore, in the technology described in Patent Document 1 below, a plurality of cooling passages extending in a certain direction are formed between the inner circumferential surface and the outer circumferential surface of the combustor cylinder, and a cooling medium is caused to flow therein. I have to.

Moreover, the combustor described in Patent Document 2 below includes a combustor tube in which fuel is combusted, and a plurality of nozzles that inject fuel into the combustor tube. The combustor tube has a cylindrical shape around the combustor axis. Here, for the convenience of the following explanation, the direction in which the combustor axis extends is referred to as the axial direction, and of both sides in this axial direction, one side is referred to as the proximal end side and the other side as the distal end side. The nozzle includes a primary fuel nozzle and a secondary fuel nozzle. The primary fuel nozzle is arranged on the proximal end side of the combustor cylinder, and injects the primary fuel into the combustor cylinder toward the distal end side. The secondary fuel nozzle is attached to the combustion tube at a position closer to the tip than the primary fuel nozzle, and injects the secondary fuel radially inward into the combustor tube.

Japanese Patent Application Publication No. 2010-261318 Japanese Patent Application Publication No. 2013-238387

As described in Patent Document 2, when a secondary fuel nozzle is attached to a combustor tube, a plurality of cooling passages formed in the combustor tube interfere with the secondary fuel nozzle. Therefore, in this case, it is difficult to reduce the temperature around the secondary fuel nozzle of the combustor tube to a certain level or less, which impairs the durability of the combustor tube. Therefore, for example, by forming a large number of cooling passages with large cross-sectional areas in the combustor cylinder and supplying a cooling medium to each cooling passage, it is possible to maintain the temperature around the secondary fuel nozzle at a constant temperature or lower. On the other hand, from the viewpoint of operating costs and the like, it is also desired to reduce the flow rate of the cooling medium supplied to the combustor cylinder as much as possible.

Therefore, an object of the present disclosure is to provide a technique that can suppress the flow rate of a cooling medium while maintaining the durability of a combustor cylinder.

A combustor cylinder as one aspect of the present disclosure for achieving the above object includes:
In a combustor cylinder having a cylindrical shape around an axis and forming a combustion space in which fuel can be combusted on the inner peripheral side, an inner peripheral surface defining a radially outer edge of the combustion space with respect to the axis; a plurality of cooling passages formed between an outer circumferential surface in a back-to-back relationship with the circumferential surface, the inner circumferential surface and the outer circumferential surface and through which a cooling medium can flow, and penetrating from the outer circumferential surface to the inner circumferential surface; The cooling medium has a detour passage formed in an annular shape around the nozzle attachment through hole along an edge of the nozzle attachment through hole and through which the cooling medium can flow. Each of the plurality of cooling passages has an inlet into which the cooling medium can flow, and an outlet through which the cooling medium can flow out. Among the plurality of cooling passages, a plurality of cooling passages that are adjacent to each other form a plurality of first cooling passages. At least some of the plurality of cooling passages form a plurality of first cooling passages that are adjacent to each other, and the plurality of cooling passages that are adjacent to each other form a plurality of second cooling passages. Each of the plurality of first cooling passages communicates with the detour passage at the respective outlet. The plurality of second cooling passages communicate with the detour passage at their respective inlets.

In this aspect, the cooling medium flows into the first cooling passage from the inlet of the first cooling passage. In the process of flowing through this first cooling passage, the cooling medium cools the area around the first cooling passage of the combustor cylinder. This cooling medium flows out from the outlet of the first cooling passage. The cooling medium flowing out of the first cooling passage flows into a detour passage formed in an annular shape around the nozzle attachment through hole and along the edge of the nozzle attachment through hole. The cooling medium that has flowed into the detour cools the area around the detour of the combustor cylinder while flowing through the detour. The cooling medium that has flowed into the detour passage flows into the second cooling passage from the entrance of the second cooling passage. The cooling medium cools the area around the second cooling passage of the combustor cylinder while flowing through the second cooling passage. This cooling medium flows out from the outlet of the second cooling passage.

Around the nozzle attachment through hole of the combustor tube, there are two types of cooling medium flowing near the outlet of the first cooling passage, a cooling medium flowing through a detour passage formed around the nozzle attachment through hole, and a cooling medium flowing near the inlet of the second cooling passage. It is cooled by the cooling medium flowing through it.

Therefore, in this aspect, the area around the nozzle attachment through hole to which the secondary fuel nozzle is attached can be cooled with the cooling medium. Moreover, in this aspect, the cooling medium that has flowed through the first cooling passage is not exhausted to the inner peripheral side of the combustor cylinder near the nozzle attachment through hole, for example, and this cooling medium is passed through the bypass passage to the second cooling passage. It leads to two cooling passages. Therefore, in this aspect, the flow rate of the cooling medium supplied to the combustor cylinder can be suppressed.

A combustor as one aspect of the present disclosure for achieving the above object includes:
Injecting the primary fuel into the combustor cylinder according to the above aspect, in a direction having a direction component toward the distal end side of the distal end side and the proximal end side in the axial direction along the axis. a secondary fuel nozzle that is attached to the combustor cylinder and that is capable of injecting secondary fuel from the nozzle attachment through hole in a direction having a radially inward component with respect to the axis; Equipped with

A gas turbine as one aspect of the present disclosure for achieving the above object includes:
The combustor according to the above aspect; a compressor capable of compressing air to generate compressed air used for combustion of fuel in the combustor cylinder; and a turbine that can be driven by combustion gas.

In one aspect of the present disclosure, even if the secondary fuel nozzle is attached to the combustor tube, the flow rate of the cooling medium can be suppressed while maintaining the durability of the combustor tube.

FIG. 1 is a schematic diagram showing the configuration of a gas turbine in an embodiment according to the present disclosure. FIG. 1 is a cross-sectional view around a combustor of a gas turbine in an embodiment according to the present disclosure. FIG. 2 is a plan view of a main part of a combustor cylinder in an embodiment according to the present disclosure. 4 is a sectional view taken along the line IV-IV in FIG. 3. FIG. 4 is a sectional view taken along the line VV in FIG. 3. FIG. 4 is a sectional view taken along the line VI-VI in FIG. 3. FIG. FIG. 7 is a plan view of a main part of a combustor cylinder in a modified example of an embodiment according to the present disclosure.

Hereinafter, embodiments of a combustor equipped with a combustor tube according to the present disclosure, a gas turbine facility equipped with the combustor, and modified examples of the combustor tube will be described in detail with reference to the drawings.

"Embodiment of gas turbine equipment"
An embodiment of gas turbine equipment will be described with reference to FIG.

As shown in FIG. 1, the gas turbine equipment in this embodiment includes a gas turbine and forced cooling equipment 16.

The gas turbine is driven by a compressor 20 that can compress outside air A to generate compressed air Acom, a plurality of combustors that can generate combustion gas G by burning fuel F in compressed air Acom, and combustion gas G. A possible turbine 30 is provided.

The compressor 20 includes a compressor rotor 21 that rotates around a rotor axis Ar, a compressor casing 25 that covers the compressor rotor 21, and a plurality of stator blade rows 26. The turbine 30 includes a turbine rotor 31 that rotates around a rotor axis Ar, a turbine casing 35 that covers the turbine rotor 31, and a plurality of stator blade rows 36. In the following, the direction in which the rotor axis Ar extends is referred to as the rotor axis direction Da, one side of both sides of the rotor axis direction Da is referred to as the upstream side of the axis Dau, and the other side is referred to as the downstream side of the axis Dad.

The compressor 20 is arranged on the upstream side Dau of the axis with respect to the turbine 30. The compressor rotor 21 and the turbine rotor 31 are located on the same rotor axis Ar, and are connected to each other to form the gas turbine rotor 11. For example, a rotor of a generator GEN is connected to this gas turbine rotor 11. The gas turbine further comprises an intermediate casing 14 arranged between the compressor casing 25 and the turbine casing 35. Compressed air from the compressor 20 flows into the intermediate casing 14 . The plurality of combustors are attached to the intermediate casing 14 in line in the circumferential direction with respect to the rotor axis Ar. Compressor casing 25, intermediate casing 14, and turbine casing 35 are connected to each other to form gas turbine casing 15.

The compressor rotor 21 includes a rotor shaft 22 that extends in the rotor axial direction Da with the rotor axis Ar as the center, and a plurality of rotor blade rows 23 attached to the rotor shaft 22. The plural rotor blade rows 23 are arranged in the rotor axial direction Da. Each rotor blade row 23 is composed of a plurality of rotor blades arranged in a circumferential direction with respect to the rotor axis Ar. Any one of the plurality of stator blade rows 26 is arranged on the downstream side Dad of each of the plurality of rotor blade rows 23 on the axis line. Each stator blade row 26 is provided inside the compressor casing 25. Each stationary blade row 26 is composed of a plurality of stationary blades arranged in a circumferential direction with respect to the rotor axis Ar.

The turbine rotor 31 includes a rotor shaft 32 that extends in the rotor axial direction Da centering on the rotor axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plural rotor blade rows 33 are arranged in the rotor axial direction Da. Each row of rotor blades 33 is composed of a plurality of rotor blades arranged in a circumferential direction with respect to the rotor axis Ar. Any one of the plurality of stator blade rows 36 is arranged on the axial upstream side Dau of each of the plurality of rotor blade rows 33 . Each stationary blade row 36 is provided inside the turbine casing 35. Each stator blade row 36 is composed of a plurality of stator blades arranged in a circumferential direction with respect to the rotor axis Ar. In the annular space between the inner circumferential side of the turbine casing 35 and the outer circumferential side of the rotor shaft 32, a region where the plurality of stator blade rows 36 and the plurality of moving blade rows 33 are arranged is a region where combustion from the combustor is disposed. A combustion gas flow path 39 through which gas G flows is formed.

A fuel line 45 is connected to the combustor. The combustor can combust fuel F from fuel line 45 in compressed air Acom from compressor 20 to generate combustion gas G.

The forced cooling equipment 16 is equipment that sends forced cooling air Acl to the high-temperature parts of the combustor that are exposed to the high-temperature combustion gas G among the parts constituting the gas turbine. This forced cooling equipment 16 has a cooling air line 17, a cooler 18, and a boost compressor 19. The cooling air line 17 is a line capable of extracting compressed air Acom from the intermediate casing 14 and guiding the compressed air Acom to high-temperature components. The cooling air line 17 includes a bleed air line 17e, a cooling air main line 17m, and a plurality of cooling air branch lines 17b. The bleed air line 17e is connected to the intermediate casing 14 and guides compressed air Acom in the intermediate casing 14 to the boost compressor 19. The cooler 18 is provided in the bleed air line 17e and can cool the compressed air Acom flowing through the bleed air line 17e. The boost compressor 19 boosts the pressure of the compressed air Acom cooled by the cooler 18 and sends this compressed air Acom to high-temperature components as forced cooling air Acl. The cooling air main line 17m is connected to the discharge port of the boost compressor 19. Forced cooling air Acl, which is air pressurized by the boost compressor 19, flows through the cooling air main line 17m. The cooling air branch line 17b is a line branched from the cooling air main line 17m for each of a plurality of high-temperature parts. Each of the plurality of cooling air branch lines 17b guides forced cooling air Acl to any one of the high-temperature components.

"Embodiment of a combustor tube and a combustor having this combustor tube"
Embodiments of a combustor tube and a combustor having the combustor tube will be described with reference to FIGS. 2 to 6.

As shown in FIG. 2, the combustor in this embodiment includes a flange 41, an inner tube 43, a combustor tube 50 (combustion tube or transition tube), a plurality of primary fuel pipes 46, and a plurality of primary fuel nozzles. 47, a secondary fuel pipe 48, a branched secondary fuel pipe 48b, a plurality of secondary fuel nozzles 49, a fuel manifold 48m, an acoustic attenuator 60, and a cooling air jacket 65.

The flange 41 extends radially from the combustor axis Ac. Both the inner cylinder 43 and the combustor cylinder 50 are arranged within the intermediate casing 14. Further, both the inner cylinder 43 and the combustor cylinder 50 have a cylindrical shape around the combustor axis Ac. Here, for convenience of the following explanation, the direction in which the combustor axis Ac (hereinafter simply referred to as the axis) extends is assumed to be the axial direction Dc. Of both sides in the axial direction Dc, one side is referred to as a distal end side Dct, and the other side is referred to as a proximal end side Dcb. Note that the distal end side Dct is the axial downstream side Dad in the rotor axial direction Da, and the base end side Dcb is the axial upstream side Dau in the rotor axial direction Da. Moreover, the axis line Ac is inclined with respect to the rotor axis line Ar so as to approach the rotor axis line Ar as it goes toward the distal end side Dct. The circumferential direction with respect to the axis Ac is simply referred to as the circumferential direction Dcc. Further, the radial direction with respect to the axis Ac is simply referred to as the radial direction Dr. The side approaching the axis Ac in the radial direction Dr is radially inner Dri, and the side opposite to this radially inner Dri is radially outer Dro.

The intermediate casing 14 is formed with a combustor attachment hole 14h that penetrates into the intermediate casing 14 from outside the intermediate casing 14. The flange 41 is attached to the intermediate casing 14 with bolts 42 so as to close the combustor attachment hole 14h. The inner cylinder 43 is attached to the flange 41. A plurality of primary fuel nozzles 47 are arranged on the inner peripheral side of this inner cylinder 43. The combustor cylinder 50 is connected to the distal end Dct portion of the inner cylinder 43 via a seal member or the like. The combustor cylinder 50 is supported by a cylinder support 44 fixed to the inner surface of the intermediate casing 14 and the like.

All of the plurality of primary fuel nozzles 47 extend in the axial direction Dc. Each of the plurality of primary fuel nozzles 47 is capable of injecting primary fuel in a direction having a directional component toward the tip side Dct. All of the plurality of primary fuel nozzles 47 are fixed to the flange 41. Among the plurality of primary fuel nozzles 47, one nozzle is a pilot nozzle 47p, and the other plurality of nozzles are main nozzles 47m. Pilot nozzle 47p is arranged on axis Ac. The plurality of main nozzles 47m are arranged in the circumferential direction Dcc around the pilot nozzle 47p.

Each of the plurality of primary fuel pipes 46 is a pipe branched from the fuel line 45 and is fixed to the flange 41. Among the plurality of primary fuel pipes 46, one primary fuel pipe 46 is a pilot fuel pipe 46p, and the other plurality of primary fuel pipes 46 are main fuel pipes 46m. Pilot fuel pipe 46p is connected to pilot nozzle 47p. Each of the plurality of main fuel pipes 46m is connected to any one of the plurality of main nozzles 47m.

The plurality of secondary fuel nozzles 49 are attached to the combustor cylinder 50 in a line in the circumferential direction Dcc at a position closer to the tip side Dct than the plurality of primary fuel nozzles 47 . All of the plurality of secondary fuel nozzles 49 are capable of injecting secondary fuel toward the radially inner side Dri into the combustor cylinder 50.

The fuel manifold 48m is disposed on the outer peripheral side of the combustor tube 50, on the distal side Dct of the primary fuel nozzle 47 and on the proximal side Dcb of the secondary fuel nozzle 49. The fuel manifold 48m is formed in an annular shape with respect to the axis Ac. The fuel manifold 48m has an annular shape with respect to the axis Ac, and forms a fuel space in which secondary fuel can be temporarily stored. The aforementioned secondary fuel pipe 48 is connected to this fuel manifold 48m. This secondary fuel pipe 48 is also a pipe branched from the fuel line 45 and is fixed to the flange 41. The fuel manifold 48m and the plurality of secondary fuel nozzles 49 are connected by a plurality of branched secondary fuel pipes 48b. Therefore, the fuel manifold 48m communicates with the plurality of secondary fuel nozzles 49 via the plurality of branched secondary fuel pipes 48b so that the secondary fuel in the fuel space can be supplied to the plurality of secondary fuel nozzles 49. There is.

As shown in FIGS. 2 and 4, the combustor tube 50 has an inner circumferential surface 50i that defines an edge of the radially outer Dro of the combustion space 50s in which fuel can be combusted, and a back-to-back relationship with the inner circumferential surface 50i. It has a certain outer circumferential surface 50o and a nozzle attachment through hole 51 penetrating from the outer circumferential surface 50o to the inner circumferential surface 50i. This combustor cylinder 50 has a cylindrical cylinder main body 52 and an outlet flange 55 around the axis Ac. The inner peripheral side of the cylinder body 52 forms the aforementioned combustion space 50s. The outlet flange 55 is provided at the end of the cylindrical body 52 on the distal end side Dct. The outlet flange 55 extends from the tip side Dct end of the cylinder body 52 toward the radially outer side Dro.

The acoustic attenuator 60 has an acoustic cover 61 that forms an acoustic space 60s on the outer peripheral side of the cylinder body 52 in cooperation with a part of the plate forming the cylinder body 52 of the combustor cylinder 50. This acoustic cover 61 is provided in a portion on the base end side Dcb of the cylinder body 52 in an annular shape with respect to the axis Ac. An acoustic hole 63 is formed in a part of the plate forming the cylinder body 52 of the combustor cylinder 50, which penetrates from the outer circumferential side of the cylinder body 52 toward the inner circumferential side.

The cooling air jacket 65 is a cover that forms a cooling air space 65s on the outer peripheral side of the cylinder body 52 in cooperation with a part of the plate forming the cylinder body 52 of the combustor cylinder 50 and the outlet flange 55. The cooling air jacket 65 is provided on the outer peripheral side of the cylinder body 52 in an annular shape with respect to the axis Ac. The cooling air branch line 17b described above with reference to FIG. 1 is connected to this cooling air jacket 65. Therefore, the forced cooling air Acl from the forced cooling equipment 16 flows into the cooling air space 65s within the cooling air jacket 65.

As shown in FIGS. 3 to 6, the nozzle attachment through hole 51 of the combustor cylinder 50 is formed in a cylindrical shape centered on a nozzle axis An extending in the radial direction Dr with respect to the axis Ac. This nozzle attachment through hole 51 is formed between the acoustic attenuator 60 and the cooling air jacket 65 in the axial direction Dc. In addition, FIG. 3 is a principal part plan view of the combustor tube 50 when the combustor tube 50 is viewed from the radially outer side Dro. FIG. 4 is a sectional view taken along the line IV-IV in FIG. 3. FIG. 5 is a sectional view taken along the line VV in FIG. 3. FIG. 6 is a sectional view taken along the line VI-VI in FIG.

The combustor cylinder 50 has a nozzle mounting seat 57 in addition to the cylinder main body 52 and the outlet flange 55 described above. The nozzle mounting seat 57 is, for example, a cylindrical member centered on the nozzle axis An, and is attached to the outer peripheral side of the cylinder body 52. Note that one end surface of both end surfaces of the nozzle attachment seat 57, which is a cylindrical member, is a nozzle attachment surface 57p to which the secondary fuel nozzle 49 is attached. This nozzle attachment surface 57p forms a part of the outer peripheral surface 50o of the combustor cylinder 50. Further, the through hole 57h of the nozzle attachment seat 57, which is a cylindrical member, forms a part of the nozzle attachment through hole 51. The cylinder body 52 of the combustor cylinder 50 is formed with a cylindrical through hole 52h extending from the outer circumferential side to the inner circumferential side thereof. This through hole 52h forms a part of the nozzle attachment through hole 51. That is, the nozzle attachment through hole 51 in this embodiment is composed of a through hole 57h in the nozzle attachment seat 57 and a through hole 52h in the cylinder body 52. The cylindrical tip of the secondary fuel nozzle 49 is inserted into the nozzle attachment through hole 51 . This nozzle mounting seat 57 has an annular detour passage 58 formed around the nozzle axis An.

The cylinder main body 52 has an outer plate 53 and an inner plate 54, as shown in FIG. Of the pair of surfaces of the outer plate 53 facing in opposite directions, one surface forms the outer circumferential surface 50o, and the other surface forms the joint surface 53c. Further, among a pair of surfaces of the inner plate 54 facing in opposite directions, one surface forms a joint surface 54c, and the other surface forms an inner circumferential surface 50i. A plurality of long grooves 53g are formed in the joint surface 53c of the outer plate 53, which are recessed toward the outer circumferential surface 50o and are long in a certain direction. The outer plate 53 and the inner plate 54 have joint surfaces 53c and 54c joined together by brazing or the like. By joining the outer plate 53 and the inner plate 54, the opening of the long groove 53g formed in the outer plate 53 is closed by the inner plate 54, and the inside of the long groove 53g becomes a cooling passage 56.

As shown in FIGS. 3 and 4, all of the plurality of cooling passages 56 extend in the axial direction Dc. Each of the plurality of cooling passages 56 has an inlet 56i through which forced cooling air ACl, which is a cooling medium ACl, can flow in, and an outlet 56o through which this forced cooling air ACl can flow out. Among the plurality of cooling passages 56, the plurality of cooling passages 56 are arranged on the tip side Dct of the nozzle axis An, have a detour passage 58 ahead of them in the direction of extension, and are adjacent to each other in the circumferential direction Dcc. constitute a plurality of first cooling passages 56a. Further, among the plurality of cooling passages 56, a detour passage 58 is disposed on the base end side Dcb with respect to the nozzle axis An, and a detour passage 58 exists at the end of the cooling passage 58 in the direction of extension thereof, and a plurality of cooling passages 58 adjacent to each other in the circumferential direction Dcc are disposed on the base end side Dcb with respect to the nozzle axis An. The cooling passage 56 forms a plurality of second cooling passages 56b.

An inlet 56i of the first cooling passage 56a is formed at the end of the tip side Dct of the first cooling passage 56a. This inlet 56i faces the cooling air space 65s. Therefore, the forced cooling air Acl in the cooling air space 65s can flow into the first cooling passage 56a. The proximal end Dcb end of the first cooling passage 56a is located in the region where the detour passage 58 exists in the axial direction Dc. An outlet 56o of the first cooling passage 56a is formed at the proximal end Dcb of the first cooling passage 56a. The outlet 56o of the first cooling passage 56a and the detour passage 58 are connected by a first communication passage 59a. The first communication passage 59a extends from the outlet 56o of the first cooling passage 56a toward the radially outer side Dro. Therefore, the forced cooling air Acl that has flowed into the first cooling passage 56a can flow into the detour passage 58 via this first communication passage 59a.

The end of the second cooling passage 56b on the distal side Dct is located in the region where the detour passage 58 exists in the axial direction Dc. An inlet 56i of the second cooling passage 56b is formed at the end of the tip side Dct of the second cooling passage 56b. The inlet 56i of the second cooling passage 56b and the detour passage 58 are connected by a second communication passage 59b. This second communication passage 59b extends from the entrance 56i of the second cooling passage 56b toward the radially outer side Dro. Therefore, the forced cooling air Acl that has flowed into the detour passage 58 can flow into the second cooling passage 56b via this second communication passage 59b. Among the plurality of second cooling passages 56b, the base end side Dcb ends of some of the second cooling passages 56b are located in the region where the acoustic cover 61 is present in the axial direction Dc. An outlet 56o of this part of the second cooling passage 56b is formed at the end of the base end side Dcb of the part of the second cooling passage 56b. This outlet 56o opens from inside the second cooling passage 56b toward the radially outer side Dro, and faces the acoustic space 60s within the acoustic cover 61. Therefore, the forced cooling air Acl that has flowed into this part of the second cooling passage 56b can flow into the acoustic space 60s. The forced cooling air Acl that has flowed into the acoustic space 60s can flow into the fuel region on the inner peripheral side of the combustor tube 50 from the acoustic hole 63. Among the plurality of second cooling passages 56b, the proximal end Dcb ends of some of the second cooling passages 56b are not located in the region where the acoustic cover 61 is present in the axial direction Dc. An outlet 56o of the other part of the second cooling passage 56b is formed at the end of the base end side Dcb of the other part of the second cooling passage 56b. This outlet 56o opens from inside the second cooling passage 56b toward the radially inner side Dri, and faces the combustion space 50s. Therefore, the forced cooling air Acl that has flowed into the other portion of the second cooling passage 56b can flow into the combustion space 50s. Therefore, the forced cooling air Acl that has flowed into all the second cooling passages 56b can flow into the combustion space 50s.

As described above, the nozzle mounting seat 57 is attached to the outer peripheral side of the cylinder body 52, and the detour passage 58 formed in the nozzle mounting seat 57 is connected to the outlet 56o of the plurality of first cooling passages 56a. and is disposed on the radially outer side Dro from the inlets 56i of the plurality of second cooling passages 56b. The cross-sectional area of the detour passage 58 is larger than the cross-sectional area of each of the plurality of first cooling passages 56a and the cross-sectional area of each of the plurality of second cooling passages 56b. Therefore, in this embodiment, the flow velocity of the forced cooling air Acl flowing through the detour passage 58 can be suppressed. Therefore, in this embodiment, the pressure loss of the forced cooling air ACl flowing through the annular detour passage 58 can be suppressed.

As shown in FIG. 3, the cross-sectional area of the detour passage 58 is determined from the central part of the detour passage 58 in the circumferential direction Dcc, that is, from the position P1 in the detour passage 58 where the nozzle axis An is the same position in the circumferential direction Dcc, to the circumferential direction. It gradually becomes larger toward the position P2 at both ends of the detour passage 58 in Dcc. In other words, the cross-sectional area of the detour passage 58 is determined from the position where the first cooling passage 56a closest to the center communicates with the detour passage 58 among the plurality of first cooling passages 56a adjacent to each other, to both ends of the detour passage 58. The first cooling passage 56a gradually becomes larger toward the position where it communicates with the detour passage 58. Further, the cross-sectional area of the detour passage 58 is determined from the position where the second cooling passages 56b at both ends communicate with the detour passage 58 to the one closest to the center among the plurality of second cooling passages 56b adjacent to each other. The second cooling passage 56b gradually becomes smaller toward the position where it communicates with the detour passage 58.

Specifically, as shown in FIG. 3, the width of the detour passage 58 varies from a position P1 in the detour passage 58 that is the same as the nozzle axis An in the circumferential direction Dcc to a position P2 at both ends of the detour passage 58 in the circumferential direction Dcc. It gets wider as you head towards it. Therefore, the width W1 at the position P1 in the detour passage 58 that is the same as the nozzle axis An in the circumferential direction Dcc becomes the minimum width of the detour passage 58, and the width W2 at the position P2 at both ends of the detour passage 58 in the circumferential direction Dcc. is the maximum width of the detour passage 58.

Further, as shown in FIG. 6, the height of the detour passage 58 in the radial direction Dr is determined from a position P1 in the detour passage 58 that is the same as the nozzle axis An in the circumferential direction Dcc to a height of both ends of the detour passage 58 in the circumferential direction Dcc. The height increases toward position P2. Therefore, the height H1 of the position P1 in the detour passage 58, which is the same as the nozzle axis An in the circumferential direction Dcc, becomes the minimum height of the detour passage 58, and the height H1 of the position P1 at both ends of the detour passage 58 in the circumferential direction Dcc is the same. The height H2 is the maximum height of the detour passage 58.

As described above, in this embodiment, the forced cooling air Acl flows into the first cooling passage 56a from the inlet 56i of the first cooling passage 56a. The forced cooling air Acl cools the area around the first cooling passage 56a of the combustor cylinder 50 while flowing through the first cooling passage 56a. This forced cooling air Acl flows out from the outlet 56o of the first cooling passage 56a. The forced cooling air Acl flowing out from the first cooling passage 56 a flows into a detour passage 58 that is formed in an annular shape around the nozzle attachment through hole 51 and along the edge of the nozzle attachment through hole 51 . The forced cooling air ACl flowing into the detour passage 58 cools the combustor tube 50 around the detour passage 58 while flowing through the detour passage 58 . The forced cooling air Acl that has flowed into the detour passage 58 flows into the second cooling passage 56b from the inlet 56i of the second cooling passage 56b. The forced cooling air Acl cools the area around the second cooling passage 56b of the combustor tube 50 while flowing through the second cooling passage 56b. This forced cooling air Acl flows out from the outlet 56o of the second cooling passage 56b.

Around the nozzle attachment through hole 51 of the combustor cylinder 50, forced cooling air Acl flows near the outlet 56o in the first cooling passage 56a, and forced cooling air ACl flows through the detour passage 58 formed around the nozzle attachment through hole 51. , and the forced cooling air ACl flowing near the inlet 56i in the second cooling passage 56b.

Therefore, in this embodiment, the area around the nozzle attachment through hole 51 to which the secondary fuel nozzle 49 is attached can be cooled with the forced cooling air Acl. Moreover, in the present embodiment, the forced cooling air Acl flowing through the first cooling passage 56a is not exhausted to the inner peripheral side of the combustor cylinder 50 near the nozzle attachment through hole 51, for example, and the forced cooling air Acl is guided to the second cooling passage 56b via the detour passage 58. Therefore, in this embodiment, the flow rate of the forced cooling air Acl supplied to the combustor cylinder 50 can be suppressed.

As described above, since the flow velocity of the cooling medium ACl flowing through the detour passage 58 is suppressed, the heat transfer coefficient between the forced cooling air ACl flowing through the detour passage 58 and the vicinity of the detour passage 58 of the combustor cylinder 50 is , the heat transfer coefficient between the forced cooling air ACl flowing through the first cooling passage 56a and the area around the first cooling passage 56a of the combustor cylinder 50, and the forced cooling air ACl flowing through the second cooling passage 56b and the second of the combustor cylinder 50. The heat transfer coefficient is lower than that with the surroundings of the cooling passage 56b. In other words, the heat transfer coefficient between the forced cooling air ACl flowing through the first cooling passage 56a and the area around the first cooling passage 56a of the combustor cylinder 50, and between the forced cooling air ACl flowing through the second cooling passage 56b and the combustor cylinder 50. The heat transfer coefficient between the second cooling passage 56b and its surroundings is higher than the heat transfer coefficient between the forced cooling air ACl flowing through the detour passage 58 and the combustor tube 50 around the detour passage 58.

Therefore, in this embodiment, the respective outlets 56o of the plurality of first cooling passages 56a and the respective inlets 56i of the plurality of second cooling passages 56b are arranged radially inner Dri than the detour passage 58, and the combustor cylinder 50, the cooling performance of the inner peripheral surface 50i of the combustor tube 50 is improved.

As described above, the cross-sectional area of the detour passage 58 gradually increases from the center of the detour passage 58 in the circumferential direction Dcc toward both ends of the detour passage 58 in the circumferential direction Dcc. Therefore, in this embodiment, forced cooling air Acl flows into the detour passage 58 from the plurality of first cooling passages 56a, and forced cooling air Acl flows out from the detour passage 58 into the plurality of second cooling passages 56b. However, the flow velocity of the forced cooling air Acl in the detour passage 58 can be made uniform. Therefore, in this embodiment, the pressure loss of the forced cooling air Acl flowing through the detour passage 58 can be suppressed. Furthermore, in this embodiment, it is possible to equalize the heat transfer coefficient between the forced cooling air Acl flowing through the detour passage 58 and the vicinity of the detour passage 58 of the combustor cylinder 50.

"Modified example of combustor tube"
The nozzle attachment through hole 51 of the combustor cylinder 50 in the above embodiment is formed into a cylindrical shape centered on the nozzle axis An extending in the radial direction Dr, in accordance with the shape of the secondary fuel nozzle 49 inserted therein. There is. However, if the shape of the portion of the secondary fuel nozzle 49 inserted into the nozzle attachment through hole 51 is square columnar, as shown in FIG. It may be formed into a quadrangular prism shape extending in the direction Dr. In this case, the detour passage 58a is annular but square shaped around the nozzle attachment through hole 51a and along the edge of the nozzle attachment through hole 51a when viewed from the radial direction Dr. Therefore, if the detour passage 58a exists 360° around the nozzle attachment through hole 51a along the edge of the nozzle attachment through hole 51a, this detour passage 58a is said to be annular. Further, as can be understood from this modification, the shape of the nozzle attachment through hole does not have to be cylindrical, and may be, for example, an elliptical cylinder or a polygonal cylinder.

In the above embodiment, forced cooling air Acl is used as the cooling medium Acl. However, the compressed air Acom in the intermediate casing 14 may be used as it is as the cooling medium Acl. In this case, the cooling air jacket 65 becomes unnecessary.

In the above embodiment, some of the exits 56o of the second cooling passages 56b open from inside the second cooling passage 56b toward the radially outer side Dro, facing the acoustic space 60s in the acoustic cover 61, and other parts An outlet 56o of the second cooling passage 56b opens toward the radially inner side Dri from inside the second cooling passage 56b, and faces the combustion space 50s. However, the exits 56o of all the second cooling passages 56b may open from the inside of the second cooling passage 56b toward the radially outer side Dro, and may face the acoustic space 60s within the acoustic cover 61. Moreover, the outlets 56o of all the second cooling passages 56b may open toward the radially inner Dri from inside the second cooling passage 56b, and may face the combustion space 50s.

In the above embodiment, the plurality of first cooling passages 56a and the detour passages 58 are connected by the plurality of first communication passages 59a, and the plurality of second cooling passages 56b and the detour passages 58 are connected by the plurality of second communication passages 59b. Connected. However, if the plurality of first cooling passages 56a and the detour passage 58 can be directly connected due to the relative positional relationship between the plurality of first cooling passages 56a and the detour passage 58, the plurality of first communication passages 59a may be omitted. You can. Further, if the plurality of second cooling passages 56b and the detour passage 58 can be directly connected due to the relative positional relationship between the plurality of second cooling passages 56b and the detour passage 58, the plurality of second communication passages 59b may be omitted. You can.

In the above embodiment, in order to change the cross-sectional area of the detour passage 58 according to the position in the detour passage 58, the width of the detour passage 58 and the height of the detour passage 58 are changed according to the position in the detour passage 58. There is. However, in order to change the cross-sectional area of the detour passage 58 depending on the position in the detour passage 58, only one of the width of the detour passage 58 and the height of the detour passage 58 may be changed.

Further, the present disclosure is not limited to the embodiment and modification described above. Various additions, changes, substitutions, partial deletions, etc. can be made without departing from the conceptual idea and spirit of the present invention derived from the content defined in the claims and equivalents thereof.

"Additional notes"
The combustor cylinder in the above embodiment can be understood, for example, as follows.

(1) The combustor cylinder in the first aspect is
In a combustor cylinder 50 that has a cylindrical shape around an axis Ac and forms a combustion space 50s in which fuel can be combusted on the inner peripheral side, an inner side that defines an edge of the radially outer Dro of the combustion space 50s with respect to the axis Ac. A circumferential surface 50i, an outer circumferential surface 50o that is in a back-to-back relationship with the inner circumferential surface 50i, and a plurality of cooling passages formed between the inner circumferential surface 50i and the outer circumferential surface 50o, through which a cooling medium ACl can flow. 56, nozzle attachment through holes 51, 51a penetrating from the outer circumferential surface 50o to the inner circumferential surface 50i, and holes extending around the nozzle attachment through holes 51, 51a along the edges of the nozzle attachment through holes 51, 51a. The detour passages 58 and 58a are formed in an annular shape and allow the cooling medium ACl to flow therethrough. Each of the plurality of cooling passages 56 has an inlet 56i into which the cooling medium ACl can flow, and an outlet 56o through which the cooling medium ACl can flow out.
At least some of the plurality of cooling passages 56 include a plurality of first cooling passages 56a that are adjacent to each other, and a plurality of second cooling passages 56b that are adjacent to each other. I will do it. The plurality of first cooling passages 56a communicate with the detour passages 58, 58a at their respective outlets 56o. The plurality of second cooling passages 56b communicate with the detour passages 58, 58a at the respective inlets 56i.

In this embodiment, the cooling medium ACl flows into the first cooling passage 56a from the inlet 56i of the first cooling passage 56a. The cooling medium ACl cools the area around the first cooling passage 56a of the combustor cylinder 50 while flowing through the first cooling passage 56a. This cooling medium ACl flows out from the outlet 56o of the first cooling passage 56a. The cooling medium ACl flowing out from the first cooling passage 56a flows into detour passages 58, 58a which are formed in an annular shape around the nozzle attachment through holes 51, 51a along the edges of the nozzle attachment through holes 51, 51a. . The cooling medium ACl that has flowed into the detour passages 58, 58a cools the surroundings of the detour passages 58, 58a of the combustor cylinder 50 while flowing through the detour passages 58, 58a. The cooling medium ACl that has flowed into the detour passages 58, 58a flows into the second cooling passage 56b from the inlet 56i of the second cooling passage 56b. The cooling medium ACl cools the area around the second cooling passage 56b of the combustor tube 50 while flowing through the second cooling passage 56b. This cooling medium ACl flows out from the outlet 56o of the second cooling passage 56b.

Around the nozzle attachment through holes 51, 51a of the combustor cylinder 50, the cooling medium ACl flowing near the outlet 56o in the first cooling passage 56a, the detour passages 58, 58a formed around the nozzle attachment through holes 51, 51a. It is cooled by the flowing cooling medium ACl and the cooling medium ACl flowing near the inlet 56i in the second cooling passage 56b.

Therefore, in this aspect, the area around the nozzle attachment through holes 51 and 51a to which the secondary fuel nozzle 49 is attached can be cooled with the cooling medium ACl. Moreover, in this embodiment, the cooling medium ACl flowing through the first cooling passage 56a is not exhausted to the inner peripheral side of the combustor tube 50 near the nozzle attachment through holes 51, 51a, for example, and this cooling medium ACl is , and is led to a second cooling passage 56b via detour passages 58, 58a. Therefore, in this aspect, the flow rate of the cooling medium ACl supplied to the combustor cylinder 50 can be suppressed.

(2) The combustor cylinder in the second embodiment is
In the combustor cylinder 50 in the first aspect, the cross-sectional area of the bypass passages 58, 58a is equal to the cross-sectional area of each of the plurality of first cooling passages 56a and the cross-sectional area of each of the plurality of second cooling passages 56b. bigger than.

In this aspect, the flow rate of the cooling medium ACl flowing through the detour passages 58, 58a can be suppressed. Therefore, in this aspect, the pressure loss of the cooling medium ACl flowing through the annular detour passages 58, 58a can be suppressed.

(3) The combustor cylinder in the third aspect is:
In the combustor cylinder 50 in the second aspect, the detour passages 58, 58a are larger than the outlet 56o of each of the plurality of first cooling passages 56a and the inlet 56i of each of the plurality of second cooling passages 56b. , are arranged on the radially outer Dro.

In this aspect as well, as described above, the cooling medium Acl flowing near the outlet 56o in the first cooling passage 56a is formed around the nozzle attachment through holes 51, 51a of the combustor cylinder 50. Cooling is performed by the cooling medium ACl flowing through the detour passages 58, 58a and the cooling medium ACl flowing near the outlet 56o in the second cooling passage 56b. Further, in this aspect as well, as described above, the flow velocity of the cooling medium ACl flowing through the detour passages 58, 58a is suppressed. Therefore, the heat transfer coefficient between the cooling medium ACl flowing through the detour passages 58, 58a and the surroundings of the detour passages 58, 58a of the combustor cylinder 50 is as follows: The heat transfer coefficient is lower than the heat transfer coefficient between the cooling passage 56a and the vicinity of the second cooling passage 56b, and the heat transfer coefficient between the cooling medium ACl flowing through the second cooling passage 56b and the second cooling passage 56b of the combustor cylinder 50. In other words, the heat transfer coefficient between the cooling medium ACl flowing through the first cooling passage 56a and the area around the first cooling passage 56a of the combustor cylinder 50, and the heat transfer coefficient between the cooling medium ACl flowing through the second cooling passage 56b and the second cooling passage 56a of the combustor cylinder 50. The heat transfer coefficient around the cooling passage 56b is higher than the heat transfer coefficient between the cooling medium ACl flowing through the detour passages 58, 58a and the vicinity of the detour passages 58, 58a of the combustor cylinder 50.

Therefore, in this aspect, the respective outlets 56o of the plurality of first cooling passages 56a and the respective inlets 56i of the plurality of second cooling passages 56b are arranged radially inner Dri than the detour passages 58, 58a, and the combustor The cooling performance of the inner peripheral surface 50i of the combustor cylinder 50 around the nozzle attachment through holes 51 and 51a of the cylinder 50 is improved.

(4) The combustor cylinder in the fourth aspect is
In the combustor cylinder 50 according to any one of the first to third aspects, the first cooling passage connects the outlet 56o of each of the plurality of first cooling passages 56a and the detour passages 58, 58a. It has a communication passage 59a and a second communication passage 59b that connects the inlet 56i of each of the plurality of second cooling passages 56b and the detour passages 58, 58a.

When the plurality of first cooling passages 56a and the detour passages 58, 58a cannot be directly connected due to the relative positional relationship between the plurality of first cooling passages 56a and the detour passages 58, 58a, the first By providing the communication passage 59a, the plurality of first cooling passages 56a and the detour passages 58, 58a can be communicated with each other. Furthermore, when the plurality of second cooling passages 56b and the detour passages 58, 58a cannot be directly connected due to the relative positional relationship between the plurality of second cooling passages 56b and the detour passages 58, 58a, as in this embodiment, By providing the second communication passage 59b, the plurality of second cooling passages 56b and the detour passages 58, 58a can be communicated with each other.

(5) The combustor cylinder in the fifth aspect is:
In the combustor cylinder 50 according to any one of the first to fourth aspects, the cross-sectional area of the detour passages 58, 58a is larger than that of the plurality of first cooling passages 56a adjacent to each other. , from the position where the first cooling passage 56a closest to the center communicates with the detour passages 58, 58a to the position where the first cooling passages 56a at both ends communicate with the detour passages 58, 58a. It's getting bigger and bigger. Further, the cross-sectional area of the detour passages 58, 58a is determined at a position where, among the plurality of second cooling passages 56b adjacent to each other, the second cooling passages 56b at both ends communicate with the detour passages 58, 58a. The second cooling passage 56b, which is closest to the center, gradually becomes smaller toward the position where it communicates with the detour passages 58, 58a.

In this aspect, even if the cooling medium Acl flows into the detour passages 58, 58a from the plurality of first cooling passages 56a, and the cooling medium ACl flows out from the detour passages 58, 58a into the plurality of second cooling passages 56b. , the flow velocity of the cooling medium ACl in the detour passages 58, 58a can be made uniform. Therefore, in this aspect, the pressure loss of the cooling medium ACl flowing through the detour passages 58, 58a can be suppressed. Furthermore, in this aspect, it is possible to equalize the heat transfer coefficient between the cooling medium ACl flowing through the detour passages 58, 58a and the surroundings of the detour passages 58, 58a of the combustor cylinder 50.

(6) The combustor tube in the sixth aspect is:
In the combustor cylinder 50 according to any one of the first to fourth aspects, the plurality of first cooling passages 56a extend in the axial direction Dc along the axis Ac, and They are arranged in the circumferential direction Dcc. In the plurality of first cooling passages 56a, the outlet 56o is formed at the end of the proximal side Dcb between the distal end side Dct and the proximal side Dcb in the axial direction Dc. The plurality of second cooling passages 56b extend in the axial direction Dc, are lined up in the circumferential direction Dcc, and are arranged closer to the base end side Dcb than the plurality of first cooling passages 56a. The plurality of second cooling passages 56b have the inlet 56i formed at the end of the distal end side Dct.

(7) The combustor cylinder in the seventh aspect is:
In the combustor cylinder 50 in the sixth aspect, the cross-sectional area of the detour passages 58, 58a is from the center of the detour passages 58, 58a in the circumferential direction Dcc to the cross-sectional area of the detour passages 58, 58a in the circumferential direction Dcc. It gradually becomes larger towards both ends.

In this aspect, even if the cooling medium Acl flows into the detour passages 58, 58a from the plurality of first cooling passages 56a, and the cooling medium ACl flows out from the detour passages 58, 58a into the plurality of second cooling passages 56b. , the flow velocity of the cooling medium ACl in the detour passages 58, 58a can be made uniform. Therefore, in this aspect, the pressure loss of the cooling medium ACl flowing through the detour passages 58, 58a can be suppressed. Furthermore, in this aspect, it is possible to equalize the heat transfer coefficient between the cooling medium ACl flowing through the detour passages 58, 58a and the surroundings of the detour passages 58, 58a of the combustor cylinder 50.

(8) The combustor tube in the eighth aspect is:
In the combustor cylinder 50 in the seventh aspect, the height of the detour passages 58, 58a in the radial direction Dr with respect to the axis Ac is from the center of the detour passages 58, 58a in the circumferential direction Dcc to the circumferential direction Dcc. The height gradually increases toward both ends of the detour passages 58, 58a.

The combustor in the above embodiment can be understood as follows, for example.
(9) The combustor in the ninth aspect is:
The combustor tube 50 according to any one of the first to eighth aspects, and the combustor tube 50 includes a distal end Dct and a proximal end Dcb in the axial direction Dc along the axis Ac. A primary fuel nozzle 47 capable of injecting primary fuel in a direction having a directional component toward the tip side Dct; A secondary fuel nozzle 49 is provided that can inject secondary fuel in a direction having a directional component toward the radially inner side Dri.

The gas turbine in the above embodiment can be understood as follows, for example.
(10) The gas turbine in the tenth aspect is:
The combustor according to the ninth aspect, the compressor 20 capable of compressing air and generating compressed air Acom used for combustion of the fuel F in the combustor cylinder 50, and the combustor 20 in the combustor cylinder 50. A turbine 30 that can be driven by combustion gas G generated by combustion of fuel is provided.

10: Gas turbine 11: Gas turbine rotor 14: Intermediate casing 14h: Combustor mounting hole 15: Gas turbine casing 16: Forced cooling equipment 17: Cooling air line 17e: Air extraction line 17m: Cooling air main line 17b: Cooling air branch line 18: Cooler 19: Boost compressor 20: Compressor 21: Compressor rotor 22: Rotor shaft 23: Moving blade row 25: Compressor casing 26: Stator blade row 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Moving blade row 35: Turbine casing 36: Stator blade row 39: Combustion gas flow path 40: Combustor 41: Flange 42: Bolt 43: Inner cylinder 44: Cylinder support 45: Fuel line 46: Primary fuel pipe 46p: Pilot fuel pipe 46m: Main fuel pipe 47: Primary fuel nozzle 47p: Pilot nozzle 47m: Main nozzle 48: Secondary fuel pipe 48b: Branch secondary fuel pipe 48m: Fuel manifold 49: Secondary fuel nozzle 50: Combustor tube (combustion tube or tailpiece)
50i: Inner circumferential surface 50o: Outer circumferential surface 50s: Combustion space 51, 51a: Nozzle attachment through hole 52: Cylinder body 52h: Through hole 53: Outer plate 53c: Joint surface 53g: Long groove 54: Inner plate 54c: Joint surface 55: Outlet flange 56: Cooling passage 56a: First cooling passage 56b: Second cooling passage 56i: Inlet 56o: Outlet 57: Nozzle mounting seat 57h: Through hole 57p: Nozzle mounting surface 58, 58a: Detour passage 59a: First communication passage 59b: Second communication passage 60: Acoustic attenuator 60s: Acoustic space 61: Acoustic cover 63: Acoustic hole 65: Cooling air jacket 65s: Cooling air space A: Outside air Acom: Compressed air Acl: Forced cooling air (cooling medium)
F: Fuel G: Combustion gas Ar: Rotor axis Ac: Combustor axis (or simply axis)
An: Nozzle axis Da: Rotor axial direction Dau: Axis upstream side Dad: Axial downstream side Dc: Axial direction Dcb: Base end side Dct: Tip side Dcc: Circumferential direction Dr: Radial direction Dri: Radial inside Dro: Radial outside

Claims (10)

In a combustor cylinder that has a cylindrical shape around the axis and forms a combustion space in which fuel can be combusted on the inner peripheral side,
an inner circumferential surface defining a radially outer edge of the combustion space with respect to the axis;
an outer circumferential surface that is in a back-to-back relationship with the inner circumferential surface;
a plurality of cooling passages formed between the inner peripheral surface and the outer peripheral surface, through which a cooling medium can flow;
a nozzle mounting through hole penetrating from the outer circumferential surface to the inner circumferential surface;
a detour passage formed in an annular shape around the nozzle attachment through hole along an edge of the nozzle attachment through hole and through which the cooling medium can flow;
has
Each of the plurality of cooling passages has an inlet through which the cooling medium can flow in, and an outlet through which the cooling medium can flow out,
At least a portion of the plurality of cooling passages constitute a plurality of first cooling passages that are adjacent to each other, and a plurality of second cooling passages that are adjacent to each other, and
each of the plurality of first cooling passages communicates with the detour passage at the respective outlet;
The plurality of second cooling passages are in communication with the detour passage at each of the inlets,
Combustor cylinder. The combustor tube according to claim 1,
The cross-sectional area of the detour passage is larger than the cross-sectional area of each of the plurality of first cooling passages and the cross-sectional area of each of the plurality of second cooling passages.
Combustor cylinder. The combustor tube according to claim 2,
The detour passage is arranged radially outward from the outlet of each of the plurality of first cooling passages and the inlet of each of the plurality of second cooling passages,
Combustor cylinder. The combustor cylinder according to any one of claims 1 to 3,
a first communication passage connecting the outlet of each of the plurality of first cooling passages and the detour passage;
a second communication passage connecting the inlet of each of the plurality of second cooling passages and the detour passage;
has,
Combustor cylinder. The combustor cylinder according to any one of claims 1 to 3,
The cross-sectional area of the detour passage is determined from the position where the first cooling passage closest to the center of the plurality of adjacent first cooling passages communicates with the detour passage, to the first cooling passage at both ends. The passage gradually becomes larger as it approaches the position where it communicates with the detour passage,
Furthermore, the cross-sectional area of the detour passage is from the position where the second cooling passages at both ends communicate with the detour passage among the plurality of second cooling passages adjacent to each other to the one closest to the center. The second cooling passage gradually becomes smaller as it approaches the position where it communicates with the detour passage.
Combustor cylinder. The combustor cylinder according to any one of claims 1 to 3,
The plurality of first cooling passages extend in an axial direction along the axis and are arranged in a circumferential direction with respect to the axis,
The plurality of first cooling passages have the outlet formed at the proximal end of the distal end side and the proximal end side in the axial direction,
The plurality of second cooling passages extend in the axial direction, are arranged in the circumferential direction, and are arranged closer to the proximal end than the plurality of first cooling passages,
The plurality of second cooling passages have the inlet formed at the end on the tip side,
Combustor cylinder. The combustor cylinder according to claim 6,
The cross-sectional area of the detour passage gradually increases from the center of the detour passage in the circumferential direction toward both ends of the detour passage in the circumferential direction.
Combustor tube. The combustor tube according to claim 7,
The height of the detour passage in the radial direction with respect to the axis is gradually increased from the center of the detour passage in the circumferential direction toward both ends of the detour passage in the circumferential direction.
Combustor tube. The combustor cylinder according to any one of claims 1 to 3,
A primary fuel nozzle capable of injecting primary fuel into the combustor cylinder in a direction having a direction component toward the distal end side of the distal end side and the proximal end side in the axial direction along the axis;
a secondary fuel nozzle attached to the combustor tube and capable of injecting secondary fuel from the nozzle attachment through hole in a direction having a radially inward component with respect to the axis;
A combustor equipped with a The combustor according to claim 9;
a compressor capable of compressing air to generate compressed air used for combustion of fuel in the combustor cylinder;
a turbine that can be driven by combustion gas generated by combustion of fuel in the combustor cylinder;
A gas turbine equipped with

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