Combustion chamber cylinder, combustion chamber and gas turbine

Abstract

A combustion chamber cylinder (50), comprising: a cylinder (50X) having a tubular shape or tube form around an axis (Ac) and forming a combustion chamber (50s) which allows the combustion of fuel (F) therein on an inner circumferential side, and a fuel nozzle (60) which is attached to the cylinder (50X) and is able to inject fuel (F) into the combustion chamber (50s) in a direction which has a directional component to a radially inward side (Dri) with respect to the axis (Ac), where the cylinder (50X) has an inner circumferential surface (50i) that defines an edge of the combustion chamber (50s) on a side (Dro) radially outward with respect to the axis (Ac), an outer circumferential surface (50o) that is in a back-to-back relationship with the inner circumferential surface (50i), a multitude of cooling passages (56) formed between the inner circumferential surface (50i) and the outer circumferential surface (50o) which allow the circulation of cooling air (ACl) through them, a nozzle mounting through-hole (51) that passes through the cylinder (50X) from the outer circumferential surface (50o) to the inner circumferential surface (50i), and a nozzle ambient passage (58) which is formed along an edge of the nozzle mounting through hole (51) around the nozzle mounting through hole (51) and allows the cooling air (Acl) to circulate through it, wherein at least a part of the plurality of cooling passages (56) is connected to the nozzle ambient passage (58), wherein the fuel nozzle (60) is attached to the cylinder (50X), while at least part of the fuel nozzle (60) is inserted through the nozzle mounting through-hole (51), wherein the fuel nozzle (60) has a mixing passage (61), a fuel passage (62) which is connected to the mixing passage (61) and is able to supply the fuel (F) into the interior of the mixing passage (61), and a connecting passage (63) which is connected to the nozzle ambient passage (58) and the mixing passage (61) of the cylinder (50X) and is able to supply cooling air (Acl) from the nozzle ambient passage (58) into the interior of the mixing passage (61), wherein the mixing passage (61) extends from a radially outward position to a radially inward position in a direction which has a component of a radial direction (Dr) with respect to the axis (Ac) and has an outlet port (61o) which is capable of injecting the fuel (F) into the combustion chamber (50s), and wherein a position in the mixing passage (61) which is connected to the connecting passage (63) is located on a side where the outlet port (61o) is located from a position where the mixing passage (61) is connected to the fuel passage (62).

Description

BACKGROUND OF THE INVENTION Area of ​​the invention

[0001] The present disclosure relates to a combustion chamber cylinder which enables the combustion of fuel in it on an inner circumferential side, a combustion chamber with this combustion chamber cylinder and a gas turbine with this combustion chamber. Description of the state of the art

[0002] A gas turbine comprises a compressor that compresses air, a combustion chamber that produces combustion gas by burning fuel using air compressed by the compressor, and a turbine that is driven by the combustion gas from the combustion chamber.

[0003] A combustion chamber has a cylinder (a combustion chamber lining or a transition piece) in which the fuel can be burned. Since an inner circumferential surface of this cylinder is exposed to the high-temperature combustion gas, the temperature of this gas becomes extremely high. Therefore, in the technology according to the following patent document 1, a multitude of cooling passages extending in a uniform direction are formed between an inner circumferential surface and an outer circumferential surface of a cylinder, and a cooling medium flows through these.

[0004] Furthermore, a combustion chamber according to the following patent document 2 comprises a cylinder in which fuel can be burned and a plurality of nozzles that inject fuel into this cylinder. The cylinder has a tubular shape around a combustion chamber axis. For simplicity, in the following description, the direction in which a combustion chamber axis extends is referred to as the axial direction. One side of the two sides in this axial direction is referred to as a base end and the other side as an outer end. The nozzles comprise a primary fuel nozzle and a secondary fuel nozzle. The primary fuel nozzle is located at the base end of the cylinder and injects primary fuel into the cylinder toward the outer end. The secondary fuel nozzle is located on the cylinder at a position on the outer end from the primary fuel nozzle and injects secondary fuel into the cylinder toward a radially inward side.Patent document 3 discloses a swirl-encapsulation fuel injection device comprising a main body having an annular section and a semi-annular section coaxially aligned with the annular section. The semi-annular section extends downstream of the annular section. An inner wall and an opposing outer wall of the main body extend between the annular and semi-annular sections. The annular section defines at least a portion of a combustion air flow path through the swirl-encapsulation fuel injection device. The semi-annular section defines a swirl-encapsulation premixing zone downstream of the combustion air flow path. The main body further defines a fuel circuit that is completely enclosed within the main body and extends between the annular section and the semi-annular section.Multiple fuel injection ports create a flow connection between the fuel circuit and the vortex-containment premixing zone. The main body can be manufactured using an additive manufacturing process.

[0005] Patent document 4 discloses a system for supplying a working fluid to a combustion chamber, comprising a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides a fluid connection so that the working fluid can flow through the flow sleeve into the combustion chamber, the tube having an axial centerline. A first set of injectors is arranged around the tube and angled radially to the axial centerline of the tube, the first set of injectors providing a fluid connection so that the working fluid can flow through a wall of the tube.

[0006] Patent document 5 discloses a staged injector in a combustion chamber of a gas turbine. The staged injector can comprise an injector tube having a side wall that encloses an injection channel extending between an outlet and an inlet. An outer segment of the injection tube can have an outer surface. A cover can be formed around the outer segment to create a surrounding antechamber. The cover can have a side wall that radially overlaps the outer segment, forming a first section of the surrounding antechamber between them. A ceiling wall of the cover can form a second section of the surrounding antechamber. A directed opening in the cover can connect the first section of the surrounding antechamber to a feed cavity.The stepped injector may include lateral guide vanes on the outer surface of the outer segment, configured to deflect a flow entering the surrounding antechamber radially towards the inlet of the injector tube.

[0007] Patent document 6 discloses that a downstream nozzle for use in a combustion chamber comprises an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall to form an annular flow space between them. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first collecting chamber adjacent to the injector tube; and, enclosed by a ceiling, a bottom situated between the inner radial wall and the outer radial wall. A feed channel may connect the first collecting chamber to an inlet formed on the outside of the outer radial wall, and baffles may be formed through the bottom of the first collecting chamber.

[0008] Patent document 7 discloses that a system for supplying fuel to a combustion chamber comprises a combustion chamber, a lining surrounding at least a portion of the combustion chamber, and a flow sleeve surrounding at least a portion of the lining. A tube provides a fluid connection so that a working fluid can flow through the flow sleeve and the lining into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provides a fluid connection so that fuel can flow through the tube wall and into the tube, and the fuel ports are not circular.

[0009] Patent document 8 discloses a method and a computer-readable model for the additive manufacturing of a channel arrangement in a combustion stage. The channel arrangement can comprise a combustion chamber wall in a combustion stage that is fluidically coupled to receive a crossflow of combustion products. An injection device can be fluidically connected to cooling fluid lines in the combustion chamber wall to receive cooling fluid flowing through the cooling fluid lines. The injection device can include means for injecting a stream of the cooling fluid, arranged to condition the interaction of a stream of reactants injected with the crossflow of combustion products. [Patent documents] [Patent Document 1] JP 2010-261318 A [Patent Document 2] JP 2013-238387 A [Patent document 3] DE 10 2015 105 235 A1 [Patent Document 4] US 9 151 500 B2 [Patent document 5] US 2017 / 0 268 785 A1 [Patent document 6] DE 10 2015 112 767 A1 [Patent document 7] US 2013 / 0 283 800 A1 [Patent document 8] US 2018 / 0 039 254 A1 SUMMARY OF THE INVENTION

[0010] In the foregoing patent document 2, since the secondary fuel is injected from the secondary fuel nozzle into the cylinder in which the primary fuel is combusting, there is a probability of a flashback phenomenon occurring, in which the secondary fuel ignites within the secondary fuel nozzle. If a flashback occurs, there is a risk of damaging the secondary fuel nozzle. For this reason, it is desirable to limit the occurrence of a flashback.

[0011] One objective of the present disclosure is therefore to provide a combustion chamber cylinder capable of mitigating the occurrence of a backfire phenomenon in which fuel ignites within a fuel nozzle, a combustion chamber with this combustion chamber cylinder, and a gas turbine with this combustion chamber.

[0012] With regard to one aspect according to the present disclosure for achieving the aforementioned objective, a combustion chamber cylinder according to independent claim 1 is provided.

[0013] Fuel flowing into the mixing passage is injected from the outlet of the mixing passage into the combustion chamber within the cylinder. The flow velocity distribution within a cross-section of the mixing passage is not uniform. The flow velocity is highest in the center of the cross-section. Conversely, the flow velocity is nearly zero in the interior of the mixing passage and near a wall surface that defines it. Therefore, even with a uniform fuel concentration distribution across the cross-section of the mixing passage, there is a probability that the fuel located near the wall surface of the mixing passage will ignite due to the influence of flames or heat in the combustion chamber of the cylinder.There is a possibility of a rebound phenomenon occurring.

[0014] In this scenario, on the side where the mixing passage's outlet is located, cooling air, which has entered through the cylinder's cooling passage, is supplied via the connecting passage from the fuel input point. Consequently, the fuel concentration on the side where the mixing passage's outlet is located decreases from the fuel input point and near the wall surface defining the mixing passage's interior. Therefore, in this scenario, the occurrence of a backfire phenomenon, where the fuel ignites within the mixing passage, can be mitigated.

[0015] According to a further aspect of the present disclosure to achieve the aforementioned objective, a combustion chamber is provided in accordance with independent claim 10.

[0016] According to another aspect of the present disclosure, to achieve the aforementioned objective, a gas turbine is provided in accordance with independent claim 11.

[0017] Advantageous modifications are contained in dependent claims 2 to 9.

[0018] According to one aspect of the present disclosure, it is possible to contain the occurrence of a backfire phenomenon in which fuel ignites inside a fuel nozzle. BRIEF DESCRIPTION OF THE DRAWINGS Fig. Figure 1 is a schematic view showing the structure of a gas turbine in an embodiment according to the present disclosure. Fig. Figure 2 is a cross-sectional view around a combustion chamber of the gas turbine in the embodiment according to the present disclosure. Fig. Figure 3 is a top view of a main section of a cylinder in the embodiment according to the present disclosure. Fig. Figure 4 is a perspective view of a main section of a combustion chamber cylinder, cut along line IV-IV in Fig. 3. Fig. Figure 5 is a cross-sectional view along line VV in Fig. 3. Fig. Figure 6 is a cross-sectional view along line VI-VI in Fig. 3. Fig. Figure 7 is a cross-sectional view of a main section of the combustion chamber cylinder in the embodiment according to the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0019] An embodiment of a combustion chamber with a combustion chamber cylinder according to the present disclosure and a gas turbine system with the combustion chamber as well as a modification example of the combustion chamber cylinder are described in detail below with reference to the drawings. Design of the gas turbine plant

[0020] One embodiment of the gas turbine plant is described with reference to Fig. 1 described.

[0021] As in Fig. As shown in Figure 1, the gas turbine plant according to the present embodiment comprises a gas turbine and a forced cooling system 16.

[0022] The gas turbine comprises a compressor 20, which can generate compressed air Acom by compressing outside air A, a plurality of combustion chambers 40, which can generate combustion gas G by burning fuel F in the compressed air Acom, and a turbine 30, which can be driven by the combustion gas G.

[0023] The compressor 20 has a compressor rotor 21 rotating about a rotor axis Ar, a compressor casing 25 covering the compressor rotor 21, and a plurality of turbine blade cascades 26. The turbine 30 has a turbine rotor 31 rotating about the rotor axis Ar, a turbine casing 35 covering the turbine rotor 31, and a plurality of turbine blade cascades 36. Hereinafter, a direction in which the rotor axis Ar extends is referred to as a rotor axis direction Da, one side of either side in this rotor axis direction Da is referred to as an axis upstream side Dau, and the other side of it is referred to as an axis downstream side Dad.

[0024] The compressor 20 is located 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, are connected to each other, and form a gas turbine rotor 11. A rotor of a generator GEN, for example, is connected to this gas turbine rotor 11. The gas turbine further comprises an intermediate casing 14, which is located between the compressor casing 25 and the turbine casing 35. Compressed air Acom from the compressor 20 flows into this intermediate casing 14. The multiple combustion chambers 40 are arranged circumferentially to the rotor axis Ar and are attached to the intermediate casing 14. The compressor casing 25, the intermediate casing 14, and the turbine casing 35 are connected to each other and form a gas turbine casing 15.

[0025] The compressor rotor 21 has a rotor shaft 22 around the rotor axis Ar, extending in the rotor axis direction Da, and a plurality of turbine blade cascades 23 attached to this rotor shaft 22. The plurality of turbine blade cascades 23 are arranged in the rotor axis direction Da. Each of the turbine blade cascades 23 is formed by a plurality of turbine blades arranged circumferentially with respect to the rotor axis Ar. Any one turbine blade cascade 26 from the plurality of turbine blade cascades 26 is arranged on the axis-downstream side Dad of each of the plurality of turbine blade cascades 23. Each of the turbine blade cascades 26 is provided on an inward side of the compressor casing 25. Each of the turbine blade cascades 26 is formed by a plurality of turbine blades arranged circumferentially with respect to the rotor axis Ar.

[0026] The turbine rotor 31 has a rotor shaft 32 extending around the rotor axis Ar in the rotor axis direction Da, and a plurality of turbine blade cascades 33 attached to this rotor shaft 32. The plurality of turbine blade cascades 33 are arranged in the rotor axis direction Da. Each of the turbine blade cascades 33 is formed by a plurality of turbine blades arranged circumferentially with respect to the rotor axis Ar. Any one turbine blade cascade 36 of the plurality of turbine blade cascades 36 is located on the axis-flow-upstream side Dau of each of the plurality of turbine blade cascades 33. Each of the turbine guide vane cascades 36 is provided on the inward side of the turbine casing 35. Each of the turbine blade cascades 36 is formed from a plurality of turbine blades arranged in the circumferential direction with respect to the rotor axis Ar.In a circular space between an inner circumferential side of the turbine housing 35 and an outer circumferential side of the rotor shaft 32, a region in which the plurality of turbine guide vane cascades 36 and the plurality of turbine blade cascades 33 are arranged forms a combustion gas flow passage 39 in which the combustion gas G flows from the combustion chamber.

[0027] Each of the combustion chambers 40 is connected to a fuel line 45. The combustion chamber 40 can generate the combustion gas G by burning the fuel F from the fuel line 45 in the compressed air Acom from the compressor 20.

[0028] The forced cooling device 16 is a device that directs forced cooling air Acl to high-temperature components of the combustion chamber that are exposed to the high-temperature combustion gas G in the components forming the gas turbine. This forced cooling device 16 comprises a cooling air duct 17, a cooler 18, and a booster or auxiliary compressor 19. The cooling air duct 17 is a duct capable of drawing the compressed air Acom from within the intermediate housing 14 and directing this compressed air Acom to the high-temperature components. The cooling air duct 17 has a draw-off line 17e, a main cooling air duct 17m, and a plurality of cooling air branch ducts 17b. The draw-off line 17e is connected to the intermediate housing 14 and directs the compressed air Acom within the intermediate housing 14 to the booster compressor 19.The cooler 18 is located in the supply line 17e and can cool the compressed air Acom flowing in this supply line 17e. The booster compressor 19 boosts or re-compresses the compressed air Acom cooled by the cooler 18 and directs this compressed air Acom as forced cooling air Acl to the high-temperature components. The main cooling air line 17m is connected to an outlet port of the booster compressor 19. The forced cooling air Acl, boosted or re-compressed by the booster compressor 19, flows in this main cooling air line 17m. The cooling air branch lines 17b are lines branching off from the main cooling air line 17m for each of the multiple high-temperature components. Each of the multiple cooling air branch lines 17b carries the forced cooling air Acl to one of the high-temperature components.

[0029] An embodiment of the combustion chamber cylinder and the combustion chamber with this combustion chamber cylinder is described with reference to the Fig. 2, Fig. 3, Fig. 4, Fig. 5 to Fig. 6 described.

[0030] As in Fig. As shown in Figure 2, the combustion chamber 40 according to the present embodiment comprises a flange 41, a combustion chamber basket 43, a combustion chamber cylinder (a combustion chamber lining or a transition piece) 50, a plurality of primary fuel lines 46, a plurality of primary fuel nozzles 47, a secondary fuel line 48, branching secondary fuel lines 48b, a fuel distributor 48m, an acoustic damping element or silencer 70 and a cooling air jacket 75.

[0031] The flange 41 extends in a radiation direction from the combustion chamber axis Ac. Both the combustion chamber basket 43 and the combustion chamber cylinder 50 are arranged within the intermediate housing 14. Furthermore, both the combustion chamber basket 43 and the combustion chamber cylinder 50 have a tubular shape around the combustion chamber axis Ac. For simplicity, in the following description, the direction in which the combustion chamber axis (hereinafter simply referred to as the axis) Ac extends is called an axial direction Dc. One of the two sides in this axial direction Dc is called an outer end Dct, and the other side is called a base end Dcb. The outer end Dct is the axis-downstream side Dad in the direction of the rotor axis Da, and the base end Dcb is the axis-upstream side Dau in the direction of the rotor axis Da.Furthermore, the axis Ac is inclined relative to the rotor axis Ar such that it approaches the rotor axis Ar in the direction of the outer end face Dct. The circumferential direction relative to the axis Ac is simply referred to as the circumferential direction Dcc. Additionally, a radial direction relative to the axis Ac is simply referred to as the radial direction Dr. A side approaching the axis Ac in this radial direction Dr is referred to as a radially inward side Dri, and a side opposite this radially inward side Dri is referred to as a radially outward side Dro.

[0032] The intermediate housing 14 has a combustion chamber mounting hole 14h that extends from the outside of the intermediate housing 14 to the inside. The flange 41 is attached to the intermediate housing 14 by bolts 42, thus closing this combustion chamber mounting hole 14h. The combustion chamber basket 43 is attached to the flange 41. The plurality of primary fuel nozzles 47 are arranged on the inner circumferential side of this combustion chamber basket 43. The combustion chamber cylinder 50 is connected to a portion of the combustion basket 43 at its outer end Dct by an intermediate sealing element or similar. The combustion chamber cylinder 50 is supported by a cylinder carrier 44 or the like, which is attached to an inner surface of the intermediate housing 14.

[0033] The combustion chamber cylinder 50 has a tubular cylinder 50X around the combustion chamber axis Ac and a plurality of secondary fuel nozzles 60 attached to this cylinder 50X. The inner circumferential side of the cylinder 50X forms a combustion chamber 50s in which the fuel can be burned. The plurality of secondary fuel nozzles 60 can inject secondary fuel F2 into the combustion chamber 50s in a direction that has a directional component towards the radially inward side Dri.

[0034] Each of the plurality of primary fuel nozzles 47 extends in the axial direction Dc. Each of the plurality of primary fuel nozzles 47 can inject primary fuel F1 in a direction that has a directional component towards the outer end Dct. Each of the plurality of primary fuel nozzles 47 is attached to the flange 41. One nozzle of the plurality of primary fuel nozzles 47 is a pilot nozzle 47p, and the plurality of the other nozzles are main nozzles 47m. The pilot nozzle 47p is arranged on the axis Ac. The plurality of main nozzles 47m are arranged around the pilot nozzle 47p in the circumferential direction Dcc.

[0035] Each of the plurality of primary fuel lines 46 is a line branching off from the fuel line 45 and is attached to the flange 41. One of the primary fuel lines 46 from the plurality of primary fuel lines 46 is a pilot fuel line 46p, and the plurality of the other primary fuel lines 46 are main fuel lines 46m. The pilot fuel line 46p is connected to the pilot nozzle 47p. Each of the plurality of main fuel lines 46m is connected to any one of the plurality of main nozzles 47m.

[0036] The multitude of secondary fuel nozzles 60 described above are arranged in the circumferential direction Dcc and are attached to positions on the outer end side Dct of the multitude of primary fuel nozzles 47 on the cylinder 50X.

[0037] The fuel distributor 48m is located on the outer circumferential side of the cylinder 50X, at the outer end Dct of the primary fuel nozzles 47, and at the base end DCB of the secondary fuel nozzles 60. The fuel distributor 48m is shaped circularly with respect to the axis Ac. It forms a fuel chamber in which the secondary fuel F2 can be temporarily stored. The secondary fuel line 48 described above is connected to this fuel distributor 48m. This secondary fuel line 48 also branches off from the fuel line 45 and is attached to the flange 41. The fuel distributor 48m and the plurality of secondary fuel nozzles 60 are interconnected by a plurality of branching secondary fuel lines 48b.Thus, the fuel distributor 48m is connected to the multitude of secondary fuel nozzles 60 via the multitude of branched secondary fuel lines 48b, so that the secondary fuel F2 can be supplied to the multitude of secondary fuel nozzles 60 within the fuel chamber.

[0038] As in the Fig. 2 and Fig. As shown in Figure 4, the cylinder 50X has an inner circumferential surface 50i, which defines an edge of the combustion chamber 50s on the radially outer side Dro, allowing the fuel to burn therein; an outer circumferential surface 50o, which is in a back-to-back relationship with the inner circumferential surface 50i; and a nozzle mounting through-hole 51, which extends through the cylinder 50X from the outer circumferential surface 50o to the inner circumferential surface 50i. This cylinder 50X is formed with a tubular cylinder main body 52 around the axis Ac and an exhaust flange 55. The inner circumferential side of the cylinder main body 52 forms the combustion chamber 50s described above. The exhaust flange 55 is provided at one end of the cylinder main body 52 on the outer end side Dct. This outlet flange 55 extends from the end of the cylinder main body 52 at the outer end side Dct to the radially outward side Dro.

[0039] The acoustic damping element 70 has an acoustic cover 71, which, together with a portion of a plate forming the cylinder body 52, forms an acoustic space 70s on the outer circumferential side of the cylinder body 52. ​​This acoustic cover 71 is circular with respect to the axis Ac on a portion of the cylinder body 52 at the base end Dcb. Acoustic holes 73, which penetrate the acoustic cover 71 from the outer circumferential side of the cylinder body 52 to the inner circumferential side, are formed in the portion of the plate forming the cylinder body 52.

[0040] The cooling air jacket 75 is a cover that, together with the part of the plate forming the cylinder main body 52 and the outlet flange 55, forms a cooling air chamber 75s on the outer circumferential side of the cylinder main body 52. ​​This cooling air jacket 75 is circular with respect to the axis Ac on the outer circumferential side of the cylinder main body 52. ​​The components described above are attached to this cooling air jacket 75. Fig. The cooling air branch lines 17b described above are connected. Thus, the forced cooling air Acl from the forced cooling device 16 flows into the cooling air space 75s within this cooling air jacket 75.

[0041] As in the Fig. 3, Fig. 4, Fig. 5 to Fig. As shown in Figure 6, the nozzle mounting through-hole 51 of the cylinder 50X is columnar around a nozzle axis An, which extends in the radial direction Dr with respect to the axis Ac. This nozzle mounting through-hole 51 is formed between the acoustic damping element 70 and the cooling air jacket 75 in the axial direction Dc. Fig. Figure 3 is a top view of a main part of cylinder 50X when cylinder 50X is viewed from the radially outside side Dro. Fig. Figure 4 is a perspective view of a main part of the combustion chamber cylinder 50, cut along line IV-IV in Fig. 3. Fig. Figure 5 is a cross-sectional view along line VV in Fig. 3. Fig. Figure 6 is a cross-sectional view along line VI-VI in Fig. 3.

[0042] In addition to the cylinder body 52 and the exhaust flange 55 described above, the cylinder 50X has a nozzle mounting seat 57. This nozzle mounting seat 57 is, for example, a cylindrical element around the nozzle axis An and is attached to the outer circumferential side of the cylinder body 52. ​​One end surface of both end surfaces of the nozzle mounting seat 57 (cylindrical element) is a nozzle mounting surface 57p, to which the secondary fuel nozzle 60 is attached. This nozzle mounting surface 57p forms part of the outer circumferential surface 50o of the cylinder 50X. Furthermore, a through-hole 57h of the nozzle mounting seat 57 (cylindrical element) forms part of the nozzle mounting through-hole 51. A column-shaped through-hole 52h is formed in the main cylinder body 52, which penetrates the main cylinder body 52 from its outer circumferential side to the inner circumferential side.This through-hole 52h forms part of the nozzle mounting through-hole 51. That is, the nozzle mounting through-hole 51 according to the present embodiment is formed from the through-hole 57h of the nozzle mounting seat 57 and the through-hole 52h of the cylinder main body 52. ​​A column-shaped outer end section 60t of the secondary fuel nozzle 60 is inserted into this nozzle mounting through-hole 51. A nozzle environment passage 58 is formed in this nozzle mounting seat 57, which is formed along an edge of the nozzle mounting through-hole 51 around the nozzle mounting through-hole 51 and allows the circulation of cooling air Acl through it. This nozzle ambient passage 58 has a circular passage 58a, which has a circular shape around the nozzle axis An, and a plurality of connecting passages 58b.The multiple connecting passages 58b are passages that extend in a radial direction with respect to the nozzle axis An and penetrate the nozzle environment passage 58 from a space within the circular passage 58a to a space within the nozzle mounting passage hole 51.

[0043] As in Fig. As shown in Figure 5, the main cylindrical body 52 has an outer plate 53 and an inner plate 54. In a pair of surfaces of the outer plate 53 facing opposite sides, one surface forms the outer circumferential surface 50o, and the other surface forms a connecting surface 53c. Furthermore, in a pair of surfaces of the inner plate 54 facing opposite sides, one surface forms a connecting surface 54c, and the other surface forms the inner circumferential surface 50i. On the connecting surface 53c of the outer plate 53, a plurality of long grooves 53g are formed, which are recessed opposite the outer circumferential surface 50o and extend in a uniform direction. As for the outer plate 53 and the inner plate 54, their connecting surfaces 53c and 54c are joined to each other by brazing or the like.Since the outer plate 53 and the inner plate 54 are connected to each other, the openings of the long grooves 53g formed in the outer plate 53 are blocked by the inner plate 54, and the inner sides of these long grooves 53g become cooling passages 56.

[0044] As in Fig. 3 and Fig. As shown in Figure 4, each of the plurality of cooling passages 56 extends in the axial direction Dc. Each of the plurality of cooling passages 56 has an inlet 56i through which the forced cooling air Acl can flow in, and an outlet 56o through which this forced cooling air Acl can flow out. In the plurality of cooling passages 56, the plurality of cooling passages 56 that are arranged on the outer end Dct of the nozzle axis An, that have the nozzle ambient passage 58 at an outer end of themselves in one direction of extension, and that lie next to each other in the circumferential direction Dcc, form a plurality of first cooling passages 56a.Furthermore, in the plurality of cooling passages 56, the plurality of cooling passages 56, which are arranged at the base end side Dcb of the nozzle axis An, have the nozzle ambient passage 58 at an outer end of themselves in the extension direction, and which lie next to each other in the circumferential direction Dcc, form a plurality of second cooling passages 56b.

[0045] The inlets 56i of these first cooling passages 56a are located at the ends of the first cooling passages 56a on the outer end face Dct. These inlets 56i face the cooling air chamber 75s. Thus, the forced cooling air Acl located in the cooling air chamber 75s can flow into these first cooling passages 56a. The ends of the first cooling passages 56a at the base end face Dcb are located in an area where the nozzle ambient passage 58 is situated in the axial direction Dc. The outlets 56o of these first cooling passages 56a are located at the ends of these first cooling passages 56a on the base end face Dcb. The outlets 56o of the first cooling passages 56a and the nozzle ambient passage 58 are connected to each other by first connecting passages 59a. These first connecting passages 59a extend from the outlets 56o of the first cooling passages 56a to the radially outward side Dro.Thus, the forced cooling air Acl flowing into the first cooling passages 56a can flow through these first connecting passages 59a into the nozzle ambient passage 58.

[0046] The ends of the second cooling passages 56b on the outer end side Dct are arranged in a region where the nozzle ambient passage 58 is located in the axial direction Dc. The inlets 56i of these second cooling passages 56b are formed at the ends of these second cooling passages 56b on the outer end side Dct. The inlets 56i of the second cooling passages 56b and the nozzle ambient passage 58 are connected to each other by second connecting passages 59b. These second connecting passages 59b extend from the inlets 56i of the second cooling passages 56b to the radially outward side Dro. In this way, the forced cooling air Acl, which has flowed into the nozzle ambient passage 58, can flow into the second cooling passages 56b through these second connecting passages 59b.

[0047] In the multiple secondary cooling passages 56b, the ends of a portion of the secondary cooling passages 56b are arranged on the base end side Dcb in an area where the acoustic cover 71 is present in the axial direction Dc. At the ends of this portion of the secondary cooling passages 56b on the base end side Dcb, outlets 56o of the portion of the secondary cooling passages 56b are formed. These outlets 56o open from the inner sides of the secondary cooling passages 56b to the radially outward side Dro and face the acoustic space 70s within the acoustic cover 71. Thus, the forced cooling air Acl flowing into this portion of the secondary cooling passages 56b can flow into the acoustic space 70s. The forced cooling air Acl, which has flowed into the acoustic space 70s, can flow from the acoustic holes 73 into the combustion chamber 50s of the cylinder 50X on the inner circumferential side.In the multiple secondary cooling passages 56b, the ends of another part of the secondary cooling passages 56b on the base end side DCB are not located in an area where the acoustic cover 71 is present in the axial direction Dc. The outlets 56o of the other part of the secondary cooling passages 56b are formed at the ends of this other part of the secondary cooling passages 56b on the base end side DCB. These outlets 56o open from the inner sides of the secondary cooling passages 56b to the radially inward side Dri and face the combustion chamber 50s. Thus, the forced cooling air Acl flowing into this other part of the secondary cooling passages 56b can flow into the combustion chamber 50s. Therefore, the forced cooling air Acl that has flowed into all secondary cooling passages 56b can flow into the combustion chamber 50s.

[0048] Since the nozzle mounting seat 57, as described above, is attached to the outer circumferential side of the cylinder body 52, the nozzle ambient passage 58 formed in this nozzle mounting seat 57 is located on the radially outer side Dro from the outlets 56o of the plurality of first cooling passages 56a and the inlets 56i of the plurality of second cooling passages 56b. The cross-sectional area of ​​this nozzle ambient 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. For this reason, in the present embodiment, the flow velocity of the forced cooling air Acl flowing into the nozzle ambient passage 58 can be controlled. Thus, in the present embodiment, a pressure loss of the forced cooling air Acl flowing into the nozzle ambient passage 58 in the circular nozzle can be dampened.

[0049] As in Fig. As shown in Figure 3, the cross-sectional area of ​​the nozzle ambient passage 58 gradually increases to positions P2 at both ends of the nozzle ambient passage 58 in the circumferential direction Dcc from a central section of the nozzle ambient passage 58 in the circumferential direction Dcc, namely positions P1, which are the same positions as the nozzle axis An in the circumferential direction Dcc in the nozzle ambient passage 58. In other words, the cross-sectional area of ​​the nozzle ambient passage 58 gradually increases to positions where the first cooling passages 56a at both ends are connected to the nozzle ambient passage 58, starting from a position where the first cooling passage 56a closest to the central section is connected to the nozzle ambient passage 58 in the plurality of adjacent first cooling passages 56a.Furthermore, the cross-sectional area of ​​the nozzle ambient passage 58 gradually decreases to a position where the second cooling passage 56b, which is closest to the central section, communicates with the nozzle ambient passage 58 from positions where the second cooling passages 56b at both ends are connected to the nozzle ambient passage 58 in the plurality of second cooling passages 56b that are adjacent to each other.

[0050] In particular, as in Fig. Figure 3 shows the width of the nozzle ambient passage 58 at positions P2 at both ends of the nozzle ambient passage 58 in the circumferential direction Dcc from positions P1, which are the same positions as the nozzle axis An in the circumferential direction Dcc in the nozzle ambient passage 58. Therefore, a width W1 at positions P1, which are the same positions as the nozzle axis An in the circumferential direction Dcc in the nozzle ambient passage 58, becomes the smallest width of the nozzle ambient passage 58, and a width W2 at positions P2 at both ends of the nozzle ambient passage 58 in the circumferential direction Dcc becomes the largest width of the nozzle ambient passage 58.

[0051] Furthermore, as in Fig. Figure 6 shows that the height of the nozzle ambient passage 58 in the radial direction Dr is greater at positions P2 at both ends of the nozzle ambient passage 58 in the circumferential direction Dcc than at positions P1, which are the same positions as the nozzle axis An in the circumferential direction Dcc within the nozzle ambient passage 58. Therefore, a height H1 at positions P1, which are the same positions as the nozzle axis An in the circumferential direction Dcc within the nozzle ambient passage 58, becomes the smallest height of the nozzle ambient passage 58, and a height H2 at positions P2 at both ends of the nozzle ambient passage 58 in the circumferential direction Dcc becomes the largest height of the nozzle ambient passage 58.

[0052] As in the Fig. 4 and Fig. As shown in Figure 7, each of the secondary fuel nozzles 60 has a columnar head section 60h and a columnar outer end section 60t. The outer diameter of this outer end section 60t is almost equal to the inner diameter of the nozzle mounting through-hole 51, so that the columnar outer end section 60t can be inserted into the nozzle mounting through-hole 51. The outer diameter of the columnar head section 60h is larger than the inner diameter of the nozzle mounting through-hole 51.

[0053] The secondary fuel nozzle 60 has a mixing passage 61 formed from the head section 60h to the outer end section 60t, a fuel passage 62 formed in the head section 60h, and a plurality of connecting passages 63 formed in the outer end section 60t.

[0054] The mixing passage 61 extends in one direction with a component in the radial direction Dr from the head section 60h to the outer end section 60t. The mixing passage 61 has a compressed air port 61i, which is capable of directing the compressed air Acom present at the outer circumferential side of the cylinder 50X into the mixing passage 61, and an exhaust port 61o, which is capable of injecting the secondary fuel F2 into the combustion chamber 50s. The compressed air port 61i is located at one end of the mixing passage 61 on the radially outward side Dro. The exhaust port 61o is located at one end of the mixing passage 61 on the radially inward side Dri.

[0055] Fuel passage 62 is connected to mixing passage 61 and can supply the secondary fuel F2 into the interior of this mixing passage 61. Around the mixing passage 61, this fuel passage 62 has a circular fuel distribution passage 62b around the nozzle axis An, a fuel intake passage 62a which is connected to the fuel distribution passage 62b and is able to send the secondary fuel F2 from the outside into the fuel distribution passage 62b, and a plurality of branch fuel passages 62c which are connected to the fuel distribution passage 62b and are able to guide the secondary fuel F2 from the fuel distribution passage 62b into the mixing passage 61. The fuel intake passage 62a is connected to the branching secondary fuel lines 48b, which are connected by means of Fig.2 were described. Each of the multiple branch fuel passages 62c has a fuel outlet 62o, which causes the secondary fuel F2, which has flowed in the branch fuel passages 62c, to flow into the interior of the mixing passage 61.

[0056] The plurality of connecting passages 63 are connected to the nozzle ambient passage 58 and the mixing passage 61 of the cylinder 50X, so that the forced cooling air Acl from the nozzle ambient passage 58 can be supplied to the interior of the mixing passage 61. In particular, when the secondary fuel nozzles 60 are attached to the cylinder 50X, each of the plurality of connecting passages 63 is connected to one of the connecting passages 58b of the nozzle ambient passage 58. Each of the plurality of connecting passages 63 has a cooling air outlet 63o through which the forced cooling air Acl flows into the interior of the mixing passage 61.

[0057] Positions in the mixing passage 61 that are connected to the connecting passages 63 are located on the side where the outlet port 61o is located, relative to a position where the mixing passage 61 is connected to the fuel passage 62. Specifically, positions in the mixing passage 61 where the cooling air outlets 63o of the connecting passages 63 are located are located on the side where the outlet port 61o is located, relative to positions where the fuel outlets 62o of the fuel passage 62 are located. In the present embodiment, the side where the outlet port 61o is located is the radially inward side Dri.

[0058] Furthermore, in the mixing passage 61, the compressed air port 61i is positioned on a side opposite the outlet port 61o, based on the position where the fuel passage 62 and the mixing passage 61 communicate with each other. In the mixing passage 61, the compressed air port 61i is positioned on a side opposite the outlet port 61o, based on the fuel outlets 62o of the fuel passage 62. In the present embodiment, a side opposite the outlet port 61o designates the radially outward side Dro.

[0059] Since the fuel passage 62, according to the present embodiment, has a plurality of branch fuel passages 62c, the secondary fuel F2 can be supplied to the interior of the mixing passage 61 from a plurality of locations. For this reason, in the present embodiment, compared to a case in which the secondary fuel F2 is supplied to the interior of the mixing passage 61 from a single location, a uniform fuel concentration distribution within the mixing passage 61 can be achieved.

[0060] The secondary fuel F2 flowing into the mixing passage 61 is mixed with the compressed air Acom, which has flowed into the mixing passage 61 from the compressed air port 61i. The secondary fuel F2 mixed with the compressed air Acom is expelled from the outlet port 61o of the mixing passage 61 into the combustion chamber 50s within the cylinder 50X. The flow velocity distribution in a cross-section of the mixing passage 61, with respect to the fluid flowing in this mixing passage 61, is not uniform. The flow velocity is highest in the center of the cross-section of the mixing passage 61. Conversely, the flow velocity is almost zero in the interior of the mixing passage 61 and near a wall surface that delimits the mixing passage 61.For this reason, even if the fuel concentration distribution in the cross-section of the mixing passage 61 is uniform, there is a probability that the secondary fuel F2, located near the wall surface bounding the mixing passage 61, will ignite due to the influence of flames or heat in the combustion chamber 50s of the cylinder 50X. Specifically, there is a possibility of a flashback phenomenon occurring.

[0061] In the present embodiment, on the side where the outlet port 61o of the mixing passage 61 is located, the forced cooling air Acl, which has passed through the first cooling passages 56a of the cylinder 50X, is supplied through the connecting passages 63. For this reason, in the present embodiment, the concentration of the secondary fuel F2 on the side where the outlet port 61o of the mixing passage 61 is located decreases from the position where the secondary fuel F2 is supplied to the inside of the mixing passage 61, and near the wall surface that defines the mixing passage 61, within the mixing passage 61. Therefore, in the present embodiment, the occurrence of a backfire phenomenon, in which the secondary fuel F2 ignites inside the mixing passage 61, can be contained.

[0062] As described above, in the present embodiment, the forced cooling air Acl flows from the inlets 56i of the first cooling passages 56a into the first cooling passages 56a. The forced cooling air Acl cools a portion around the first cooling passages 56a of the cylinder 50X as it flows within these first cooling passages 56a. This forced cooling air Acl flows out of the outlets 56o of the first cooling passages 56a. The forced cooling air Acl that has exited the first cooling passages 56a flows into the nozzle ambient passage 58, which is formed around the nozzle mounting through-hole 51. The forced cooling air Acl, which has flowed into the nozzle ambient passage 58, cools a portion around the nozzle ambient passage 58 of the cylinder 50X during a flow process in this nozzle ambient passage 58. The forced cooling air Acl, which has flowed into the nozzle ambient passage 58, flows from the inlets 56i of the second cooling passages 56b into the second cooling passages 56b.The forced cooling air Acl cools a portion around the second cooling passages 56b of the cylinder 50X as it flows through these second cooling passages 56b. This forced cooling air Acl flows out of the outlets 56o of the second cooling passages 56b.

[0063] A part around the nozzle mounting through-hole 51 of the cylinder 50X is cooled by the forced cooling air Acl flowing near the outlets 56o in the first cooling passages 56a, the forced cooling air Acl flowing in the nozzle ambient passage 58 formed around the nozzle mounting through-hole 51, and the forced cooling air Acl flowing near the inlets 56i in the second cooling passages 56b.

[0064] Thus, in the present embodiment, a section around the nozzle mounting through-hole 51, where the secondary fuel nozzles 60 are attached, can be cooled with the forced cooling air Acl. Furthermore, in the present embodiment, the forced cooling air Acl flowing in the first cooling passages 56a is directed through the nozzle ambient passage 58 to the second cooling passages 56b. Therefore, in the present embodiment, the flow rate of the forced cooling air Acl supplied to the cylinder 50X can be controlled.

[0065] Since, as described above, the flow velocity of the forced cooling air Acl flowing in the nozzle ambient passage 58 is controlled, the heat transfer coefficient between the forced cooling air Acl flowing in the nozzle ambient passage 58 and a part around the nozzle ambient passage 58 of the cylinder 50X is lower than the heat transfer coefficient between the forced cooling air Acl flowing in the first cooling passages 56a and a part around the first cooling passages 56a of the cylinder 50X, and the heat transfer coefficient between the forced cooling air Acl flowing in the second cooling passages 56b and a part around the second cooling passages 56b of the cylinder 50X.In other words, the heat transfer coefficient between the forced cooling air Acl flowing in the first cooling passages 56a and a portion around the first cooling passages 56a of the cylinder 50X, and the heat transfer coefficient between the forced cooling air Acl flowing in the second cooling passages 56b and a portion around the second cooling passages 56b of the cylinder 50X, is higher than the heat transfer coefficient between the forced cooling air Acl flowing in the nozzle ambient passage 58 and a portion around the nozzle ambient passage 58 of the cylinder 50X.

[0066] Therefore, in the present embodiment, 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 inward side Dri of the nozzle ambient passage 58, and the cooling performance around the nozzle mounting passage 51 of the cylinder 50X and on the inner circumferential surface 50i of the cylinder 50X is improved.

[0067] As described above, the cross-sectional area of ​​the nozzle ambient passage 58 gradually increases in the circumferential direction Dcc towards the two end sections of the nozzle ambient passage 58, starting from the central section of the nozzle ambient passage 58 in the circumferential direction Dcc. For this reason, in the present embodiment, even when the forced cooling air Acl flows into the nozzle ambient passage 58 from the plurality of first cooling passages 56a and flows out of this nozzle ambient passage 58 towards the inner surfaces of the plurality of second cooling passages 56b, a uniform flow velocity of the forced cooling air Acl within the nozzle ambient passage 58 can be achieved. Thus, in the present embodiment, a pressure loss of the forced cooling air Acl flowing in the nozzle ambient passage 58 can be minimized.Furthermore, in the present embodiment, a uniform heat transfer coefficient can be achieved between the forced cooling air Acl flowing in the nozzle ambient passage 58 and a part around the nozzle ambient passage 58 of the cylinder 50X. Example of a modification

[0068] The fuel passage 62 of the preceding embodiment comprises the fuel intake passage 62a, the circular fuel distribution passage 62b, and a plurality of branch fuel passages 62c branching off from the fuel distribution passage 62b. However, the fuel passages can also have non-circular distribution passages. In this case, the fuel passages only need to have a plurality of passages that receive the fuel from the outside and allow the fuel to flow into the interior of the mixing passage 61.

[0069] In the above embodiment, the forced cooling air Acl is used as cooling air. However, the compressed air Acom inside the intermediate housing 14 or the air obtained by tapping and cooling the compressed air Acom inside the intermediate housing 14 can also be used as cooling air.

[0070] In the foregoing embodiment, the outlets 56o of a portion of the second cooling passages 56b open from the inner sides of the second cooling passages 56b to the radially outward side Dro and face the acoustic chamber 70s within the acoustic cover 71, and the outlets 56o of another portion of the second cooling passages 56b open from the inner sides of the second cooling passages 56b to the radially inward side Dri and face the combustion chamber 50s. However, the outlets 56o of all second cooling passages 56b can open from the inner sides of the second cooling passages 56b to the radially outward side Dro and face the acoustic chamber 70s within the acoustic cover 71. Furthermore, the outlets 56o of all second cooling passages 56b can open from the inner sides of the second cooling passages 56b towards the radially inward side Dri and be directed towards the combustion chamber 50s.

[0071] In the preceding embodiment, the plurality of first cooling passages 56a and the nozzle ambient passage 58 are connected to each other by a plurality of first connecting passages 59a, and the plurality of second cooling passages 56b and the nozzle ambient passage 58 are connected to each other by a plurality of second connecting passages 59b. However, if the plurality of first cooling passages 56a and the nozzle ambient passage 58 can be directly connected to each other due to a relative positional relationship between the plurality of first cooling passages 56a and the nozzle ambient passage 58, the plurality of first connecting passages 59a can be omitted.Furthermore, if the plurality of second cooling passages 56b and the nozzle ambient passage 58 can be directly connected due to a relative positional relationship between the plurality of second cooling passages 56b and the nozzle ambient passage 58, the plurality of second connecting passages 59b can be omitted.

[0072] In the foregoing embodiment, in order to change the cross-sectional area of ​​the nozzle ambient passage 58 depending on the position within the nozzle ambient passage 58, the width and height of the nozzle ambient passage 58 are changed depending on the position within the nozzle ambient passage 58. However, to change the cross-sectional area of ​​the nozzle ambient passage 58 depending on the position within the nozzle ambient passage 58, only one of the width and height of the nozzle ambient passage 58 can be changed.

[0073] Furthermore, the present disclosure is not limited to the embodiment and modification example described above. Various additions, modifications, substitutions, partial omissions, and the like may be made within a scope that does not deviate from the conceptual idea and core of the present invention as defined in the details and equivalents specified in the claims. Attachment

[0074] The combustion chamber cylinder 50 according to the embodiment and modification example described above is determined, for example, as follows. (1) A combustion chamber cylinder according to a first aspect comprises a cylinder 50X having a tubular shape or tube shape about an axis Ac and forming a combustion chamber 50s which enables combustion of fuel F therein on an inner circumferential side, and a fuel nozzle 60 which is attached to the cylinder 50X and which can inject the fuel F2 into the combustion chamber 50s in a direction which has a directional component to a radially inward side Dri with respect to the axis Ac.The cylinder 50X has an inner circumferential surface 50i that defines an edge of the combustion chamber 50s on a radially outward side Dro with respect to the axis Ac, an outer circumferential surface 50o that has a back-to-back relationship with the inner circumferential surface 50i, a plurality of cooling passages 56 formed between the inner circumferential surface 50i and the outer circumferential surface 50o that allow the circulation of cooling air Acl through them, a nozzle mounting passage 51 that penetrates the cylinder 50X from the outer circumferential surface 50o to the inner circumferential surface 50i, and a nozzle ambient passage 58 formed along an edge of the nozzle mounting passage 51 around the nozzle mounting passage 51 through which the cooling air Acl can circulate. At least some of the multiple cooling passages 56 are connected to the nozzle ambient passage 58.The fuel nozzle 60 is attached to the cylinder 50X, with at least part of the fuel nozzle 60 inserted through the nozzle mounting through-hole 51. The fuel nozzle 60 has a mixing passage 61, a fuel passage 62 which is connected to the mixing passage 61 and is capable of supplying the fuel F2 into the interior of the mixing passage 61, and a connecting passage 63 which is connected to the nozzle ambient passage 58 and the mixing passage 61 of the cylinder 50X and is capable of supplying the cooling air Acl from the nozzle ambient passage 58 into the interior of the mixing passage 61. The mixing passage 61 extends in a direction that has a component of a radial direction Dr with respect to the axis Ac and has an outlet port 61o which is capable of injecting the fuel F2 into the combustion chamber 50s.A position in the mixing passage 61, which is connected to the connecting passage 63, is located on a side where the outlet connection 61o is present from a position where the mixing passage 61 is connected to the fuel passage 62.

[0075] The fuel F2, which has flowed into the mixing passage 61, is injected from the outlet port 61o of the mixing passage 61 into the combustion chamber 50s within the cylinder 50X. The flow velocity distribution within a cross-section of the mixing passage 61, referring to the fluid flowing in this mixing passage 61, is not uniform. The flow velocity is highest in the center of the cross-section of the mixing passage 61. Conversely, the flow velocity is nearly zero in the interior of the mixing passage 61 and near a wall surface that delimits the mixing passage 61.For this reason, even with a uniform distribution of the fuel concentration in the cross-section of the mixing passage 61, there is a probability that the fuel F2 located near the wall surface bounding the mixing passage 61 will ignite within the mixing passage 61 due to the influence of flames or heat in the combustion chamber 50s of the cylinder 50X. Specifically, there is a possibility of a flashback phenomenon occurring.

[0076] In the present aspect, on the side where the outlet port 61o of the mixing passage 61 is located, the cooling air Acl, which has passed through the cooling passages 56 of the cylinder 50X, is supplied through the connecting passage 63 from a position where the fuel F2 is supplied to the interior of the mixing passage 61. For this reason, in the present aspect, the concentration of fuel F2 on the side where the outlet port 61o of the mixing passage 61 is located decreases from a position where the fuel F2 is supplied to the interior of the mixing passage 61 and in the vicinity of the wall surface within the mixing passage 61 that delimits the mixing passage 61. Therefore, in the present aspect, the occurrence of a backfire phenomenon, in which the fuel F2 ignites inside the mixing passage 61, can be contained.

[0077] (2) As regards the combustion chamber cylinder according to a second aspect, the mixing passage 61 in the combustion chamber cylinder 50 according to the first aspect has a compressed air port 61i capable of directing the compressed air Acom present on an outer circumferential side of the cylinder 50X into the mixing passage 61. In the mixing passage 61, the compressed air port 61i is located on a side opposite the outlet port 61o, with respect to the position where the fuel passage 62 and the mixing passage 61 are connected.

[0078] In this aspect, the fuel F2, which has flowed into the mixing passage 61, is mixed with the compressed air Acom, which has flowed into the mixing passage 61 from the compressed air port 61i. In this aspect, the fuel F2 mixed with the compressed air Acom can be expelled from the exhaust port 61o of the mixing passage 61 into the combustion chamber 50s within the cylinder 50X.

[0079] (3) As regards the combustion chamber cylinder according to a third aspect, the fuel passage 62 in the combustion chamber cylinder 50 according to the first aspect or the second aspect has a circular fuel distribution passage 62b formed around the mixing passage 61, a fuel intake passage 62a connected to the fuel distribution passage 62b and capable of directing fuel F2 from the outside to the fuel distribution passage 62b, and a plurality of branch fuel passages 62c connected to the fuel distribution passage 62b and capable of directing the fuel F2 from the fuel distribution passage 62b to the mixing passage 61.

[0080] Since the fuel passage 62 has a plurality of branch fuel passages 62c, the fuel F2 can be supplied to the interior of the mixing passage 61 from a plurality of points in the present aspect. For this reason, in the present aspect, compared to a case in which the fuel F2 is supplied to the interior of the mixing passage 61 from a (single) point, a uniform fuel concentration distribution within the mixing passage 61 can be achieved.

[0081] (4) As regards the combustion chamber cylinder according to a fourth aspect, in the combustion chamber cylinder 50, according to any aspect of the first aspect up to the third aspect, each of the plurality of cooling passages 56 has an inlet 56i through which the cooling air Acl can flow in, and an outlet 56o through which the cooling air Acl can flow out. At least some of the plurality of cooling passages 56 form a plurality of first cooling passages 56a adjacent to one another and a plurality of second cooling passages 56b adjacent to one another. Each of the plurality of first cooling passages 56a is connected to the nozzle ambient passage 58 at its outlet 56o. Each of the plurality of second cooling passages 56b is connected to the nozzle ambient passage 58 at its inlet 56i.

[0082] In this aspect, the cooling air Acl flows within the nozzle ambient passage 58, which is formed around the nozzle mounting hole 51 with the fuel nozzle 60 attached thereto. Therefore, in this aspect, a portion around the nozzle mounting hole 51, where the fuel nozzle 60 is attached, can be cooled by the cooling air Acl. Furthermore, in this aspect, the cooling air Acl that has flowed through the first cooling passages 56a is directed through the nozzle ambient passage 58 to the second cooling passages 56b. Thus, in this aspect, the flow rate of the cooling air Acl supplied to the cylinder 50X can be controlled.

[0083] (5) As regards the combustion chamber cylinder according to a fifth aspect, in the combustion chamber cylinder 50 according to the fourth aspect, the cross-sectional area of ​​the nozzle surrounding the 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. The nozzle surrounding passage 58 is located on the radially outward side Dro of 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.

[0084] In the present aspect, the cross-sectional area of ​​the nozzle ambient 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. For this reason, in the present aspect, a pressure loss of the cooling air Acl flowing in the nozzle ambient passage 58 can be dampened by controlling the flow velocity of the cooling air Acl flowing in the nozzle ambient passage 58.

[0085] Therefore, the heat transfer coefficient between the cooling air Acl flowing in the nozzle ambient passage 58 and a part around the nozzle ambient passage 58 of the cylinder 50X will be lower than the heat transfer coefficient between the cooling air Acl flowing in the first cooling passages 56a and a part around the first cooling passages 56a of the cylinder 50X, and the heat transfer coefficient between the cooling air Acl flowing in the second cooling passages 56b and a part around the second cooling passages 56b of the cylinder 50X.In other words, the heat transfer coefficient between the cooling air Acl flowing in the first cooling passages 56a and a portion around the first cooling passages 56a of the cylinder 50X, and the heat transfer coefficient between the cooling air Acl flowing in the second cooling passages 56b and a portion around the second cooling passages 56b of the cylinder 50X, is higher than the heat transfer coefficient between the cooling air Acl flowing in the nozzle ambient passage 58 and a portion around the nozzle ambient passage 58 of the cylinder 50X.

[0086] Therefore, in the present aspect, 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 inward side Dri of the nozzle ambient passage 58, and the cooling performance around the nozzle mounting passage 51 of the cylinder 50X and on the inner circumferential surface 50i of the cylinder 50X is improved.

[0087] (6) As regards the combustion chamber cylinder according to a sixth aspect, in the combustion chamber cylinder 50 according to the fourth aspect or the fifth aspect, a cross-sectional area of ​​the nozzle ambient passage 58 gradually increases in the direction of a position in which the first cooling passages 56a at both ends are connected to the nozzle ambient passage 58, from a position in which the first cooling passage 56a of the plurality of first cooling passages 56a which are adjacent to each other is closest to a central section connected to the nozzle ambient passage 58.Furthermore, the cross-sectional area of ​​the nozzle ambient passage 58 gradually decreases in the direction of a position where the second cooling passages 56b, which are closest to the central section, are connected to the nozzle ambient passage 58 from a position where the second cooling passages 56b of the plurality of second cooling passages 56b, which are adjacent to each other, are connected to the nozzle ambient passage 58 at both ends.

[0088] In this aspect, even when the cooling air Acl flows from the plurality of first cooling passages 56a into the nozzle ambient passage 58 and flows out of this nozzle ambient passage 58 into the interior of the plurality of second cooling passages 56b, a uniform flow velocity of the cooling air Acl within the nozzle ambient passage 58 can be achieved. Therefore, in this aspect, a pressure drop of the cooling air Acl flowing in the nozzle ambient passage 58 can be dampened. Furthermore, in this aspect, a uniform heat transfer coefficient can be achieved between the cooling air Acl flowing in the nozzle ambient passage 58 and a portion surrounding the nozzle ambient passage 58 of the cylinder 50X.

[0089] (7) Regarding the combustion chamber cylinder according to a seventh aspect, in the combustion chamber cylinder 50, according to any aspect of the fourth to sixth aspects, the plurality of first cooling passages 56a extends in an axial direction Dc along the axis Ac and is arranged in a circumferential direction Dcc with respect to the axis Ac. In the plurality of first cooling passages 56a, the outlet 56o is formed at one end on a base end Dcb, an outer end Dct, and the base end Dcb in the axial direction Dc. The plurality of second cooling passages 56b extend in the axial direction Dc, are arranged in the circumferential direction Dcc, and are located at the base end Dcb of the plurality of first cooling passages 56a. In the plurality of second cooling passages 56b, the inlet 56i is formed at one end on the outer end Dct.

[0090] (8) As regards the combustion chamber cylinder according to an eighth aspect, in the combustion chamber cylinder 50 according to the seventh aspect, the cross-sectional area of ​​the nozzle ambient passage 58 increases from a central section of the nozzle ambient passage 58 in the circumferential direction Dcc to both end sections of the nozzle ambient passage 58 in the circumferential direction Dcc.

[0091] In this aspect, a uniform flow velocity of the cooling air Acl within the nozzle ambient passage 58 can be achieved, even when the cooling air Acl flows into the nozzle ambient passage 58 from the plurality of first cooling passages 56a and flows out of this nozzle ambient passage 58 into the interior of the plurality of second cooling passages 56b. Therefore, in this aspect, a pressure drop of the cooling air Acl flowing in the nozzle ambient passage 58 can be dampened. Furthermore, in this aspect, a uniform heat transfer coefficient can be achieved between the cooling air Acl flowing in the nozzle ambient passage 58 and a portion around the nozzle ambient passage 58 of the cylinder 50X.

[0092] (9) As regards the combustion chamber cylinder according to a ninth aspect, in the combustion chamber cylinder 50 according to the eighth aspect, the height of the nozzle ambient passage 58 in the radial direction Dr with respect to the axis Ac gradually increases to both end sections of the nozzle ambient passage 58 in the circumferential direction Dcc from the central section of the nozzle ambient passage 58 in the circumferential direction Dcc.

[0093] A combustion chamber 40 according to the embodiment and modification example described above is determined, for example, as follows.

[0094] (10) A combustion chamber according to a tenth aspect comprises the combustion chamber cylinder 50 according to any aspect of the first aspect through the ninth aspect and a primary fuel nozzle 47 capable of injecting primary fuel F1 in a direction with a directional component towards an outer end Dct from the outer end Dct and a base end Dcb in an axial direction Dc along the axis Ac within the cylinder 50X. The fuel nozzle 60 of the combustion chamber cylinder 50 is a secondary fuel nozzle capable of injecting secondary fuel F2.

[0095] A gas turbine 10 according to the embodiment and the modification example described above is determined, for example, as follows.

[0096] (11) A gas turbine according to an eleventh aspect comprises the combustion chamber 40 according to the tenth aspect, a compressor 20 capable of generating compressed air Acom, which is used for the combustion of fuel inside the cylinder 50X by compressing air A, and a turbine 30 capable of being driven by means of the combustion gas G resulting from the combustion of fuel inside the cylinder 50X EXPLANATION OF REFERENCES 10 Gas turbine 11 Gas turbine rotor 14 intermediate housings 14h Mounting hole for the combustion chamber 15 gas turbine casings 16 Forced cooling system 17 Cooling air duct 17e Dispensing line 17m cooling air main duct 17b Cooling air bypass 18 coolers 19 booster compressors 20 compressors 21 Compressor rotor 22 Rotor shaft 23 Turbine blade cascade 25 compressor housings 26 Turbine blade cascade 30 Turbine 31 Turbine rotor 32 Rotor shaft 33 Turbine blade cascade 35 turbine housings 36 Turbine blade cascade 39 Combustion gas flow passage 40 Combustion chamber 41 Flange 42 bolts 43 Combustion chamber basket 44 cylinder carriers 45 Fuel line 46 Primary fuel line 46p pilot fuel line 46m main fuel line 47 Primary fuel nozzle 47p pilot nozzle 47m main nozzle 48 Secondary fuel line 48b Branched secondary fuel line 48m fuel distributor 50 combustion chamber cylinders (combustion chamber lining or transition piece) 50X cylinder 50i inner circumferential surface 50° outer circumferential surface 50s combustion chamber 51 Nozzle mounting through hole 52 Main body of the cylinder 52h through hole 53 Outer plate 53c connection surface 53g Long Groove 54 Inner plate 54c connection surface 55 Outlet flange 56 Cooling passage 56a First cooling cycle 56b Second cooling cycle 56i Inlet 56° outlet 57 nozzle seat 57h Through hole 57p nozzle mounting surface 58 Nozzle ambient passage 58a Circular passage 58b Connecting passage 59a First connecting passage 59b Second connecting passage 60 Secondary fuel nozzle (or simply fuel nozzle) 60h head section 60t outer end section 61 Mixing pass 61i connection for compressed air 61o outlet 62 Fuel passage 62a Fuel intake pass 62b Fuel distribution passage 62c Branch fuel passage 62° Fuel outlet 63 Connecting passage 63° Cooling air outlet 70 acoustic damping element or silencer 70s acoustic room 71 Acoustic cover 73 Acoustic hole 75 Cooling air jacket 75s cooling air space Outside air (or simply: air) Acom compressed air ACL forced air cooling (or simply air) Fuel F1 Primary Fuel F2 Secondary Fuel G Combustion gas Ar Rotor axis Ac combustion chamber axis (or simply: axis) On nozzle axis Since rotor axis direction Dau axis upstream side Dad Axis Downstream Side DC Axial direction DCB Basic End Page DCT outer end DCC circumferential direction Dr. Radiale direction Dri Radial one-way side Dro Radial outside side

Claims

A combustion chamber cylinder (50) comprising: a cylinder (50X) having a tubular shape around an axis (Ac) and forming a combustion chamber (50s) that enables the combustion of fuel (F) therein on an inner circumferential side, and a fuel nozzle (60) attached to the cylinder (50X) and capable of injecting fuel (F) into the combustion chamber (50s) in a direction having a directional component towards a radially inward side (Dri) with respect to the axis (Ac), wherein the cylinder (50X) has an inner circumferential surface (50i) defining an edge of the combustion chamber (50s) on a side (Dro) radially outward with respect to the axis (Ac), an outer circumferential surface (50o) in a back-to-back relationship with the inner circumferential surface (50i), and a plurality of cooling passages (56).which are formed between the inner circumferential surface (50i) and the outer circumferential surface (50o) and allow the circulation of cooling air (Acl) through them, a nozzle mounting through-hole (51) that penetrates the cylinder (50X) from the outer circumferential surface (50o) to the inner circumferential surface (50i), and a nozzle ambient passage (58) that is formed along an edge of the nozzle mounting through-hole (51) around the nozzle mounting through-hole (51) and allows the cooling air (Acl) to circulate through it, wherein at least a part of the plurality of cooling passages (56) is connected to the nozzle ambient passage (58), wherein the fuel nozzle (60) is attached to the cylinder (50X), while at least a part of the fuel nozzle (60) is inserted through the nozzle mounting through-hole (51), wherein the fuel nozzle (60) a mixing pass (61), a fuel pass (62),which is connected to the mixing passage (61) and is able to supply the fuel (F) into the interior of the mixing passage (61), and has a connecting passage (63) which is connected to the nozzle ambient passage (58) and the mixing passage (61) of the cylinder (50X) and is able to supply cooling air (Acl) from the nozzle ambient passage (58) into the interior of the mixing passage (61), wherein the mixing passage (61) extends from a radially outward position to a radially inward position in a direction which has a component of a radial direction (Dr) with respect to the axis (Ac), and has an outlet port (61o) which is able to inject the fuel (F) into the combustion chamber (50s), and wherein a position in the mixing passage (61) which is connected to the connecting passage (63) is located on a side on which the Outlet connection (61o) is available from one position,where the mixing passage (61) is connected to the fuel passage (62). The combustion chamber cylinder (50) according to claim 1, wherein the mixing passage (61) has a connection for compressed air (61i) which is able to direct compressed air (Acom) present on an outer circumferential side of the cylinder (50X) into the mixing passage (61), and wherein in the mixing passage (61) the connection for compressed air (61i) is positioned on a side opposite the outlet port (61o), based on the position where the fuel passage (62) and the mixing passage (61) are connected. The combustion chamber cylinder (50) according to claim 1, wherein the fuel passage (62) has a circular fuel distribution passage (62b) formed around the mixing passage (61), a fuel intake passage (62a) connected to the fuel distribution passage (62b) and capable of sending fuel (F) from outside to the fuel distribution passage (62b), and a plurality of branch fuel passages (62c) connected to the fuel distribution passage (62b) and capable of directing fuel (F) from the fuel distribution passage (62b) to the mixing passage (61). The combustion chamber cylinder (50) according to one of claims 1 to 3, wherein each of the plurality of cooling passages (56) has an inlet (56i) through which the cooling air (Acl) can flow in and an outlet (56o) through which the cooling air (Acl) can flow out, wherein at least part of the plurality of cooling passages (56) forms a plurality of first cooling passages (56a) adjacent to each other and a plurality of second cooling passages (56b) adjacent to each other, wherein each of the plurality of first cooling passages (56a) is connected to the nozzle ambient passage (58) at its outlet (56o), and wherein each of the plurality of second cooling passages (56b) is connected to the nozzle ambient passage (58) at its inlet (56i). The combustion chamber cylinder (50) according to claim 4, wherein a cross-sectional area of ​​the nozzle ambient passage (58) is larger than a cross-sectional area of ​​each of the plurality of first cooling passages (56a) and a cross-sectional area of ​​each of the plurality of second cooling passages (56b), and wherein the nozzle ambient passage (58) is arranged on the radially outward side (Dro) of 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). The combustion chamber cylinder (50) according to claim 4, wherein a cross-sectional area of ​​the nozzle ambient passage (58) gradually increases to a position in which the first cooling passages (56a) are in contact with the nozzle ambient passage (58) at both ends, starting from a position in which the first cooling passage (56a) of the plurality of first cooling passages (56a) that are adjacent to each other is in contact with the nozzle ambient passage (58) closest to a central section, and wherein furthermore the cross-sectional area of ​​the nozzle ambient passage (58) gradually decreases to a position in which the second cooling passage (56b) that is closest to the central section is in contact with the nozzle ambient passage (58) from a position in which the second cooling passages (56b) of the plurality of second cooling passages (56b) that are adjacent to each other are in contact with the nozzle ambient passage (58) at both ends. The combustion chamber cylinder (50) according to claim 4, wherein the plurality of first cooling passages (56a) extend in an axial direction (Dc) along the axis (Ac) and are arranged in a circumferential direction (Dcc) with respect to the axis (Ac), wherein in the plurality of first cooling passages (56a) the outlet (56o) is formed at one end on a base end side (Dcb) from an outer end side (Dct) and the base end side (Dcb) in the axial direction (Dc), wherein the plurality of second cooling passages (56b) extend in the axial direction (Dc), are arranged in the circumferential direction (Dcc) and are arranged at the base end side (Dcb) of the plurality of first cooling passages (56a), and wherein in the plurality of second cooling passages (56b) the inlet (56i) is formed at one end on the outer end side (Dct). The combustion chamber cylinder (50) according to claim 7, wherein a cross-sectional area of ​​the nozzle ambient passage (58) gradually increases from a central section of the nozzle ambient passage (58) in the circumferential direction (Dcc) to both end sections of the nozzle ambient passage (58) in the circumferential direction (Dcc). The combustion chamber cylinder (50) according to claim 8, wherein the height of the nozzle ambient passage (58) in the radial direction (Dr) with respect to the axis (Ac) gradually increases from the central section of the nozzle ambient passage (58) in the circumferential direction (Dcc) to both end sections of the nozzle ambient passage (58) in the circumferential direction (Dcc). A combustion chamber (40) comprising: the combustion chamber cylinder (50) according to any one of claims 1 to 3, and a primary fuel nozzle (47) capable of injecting primary fuel (F1) in a direction having a directional component to an outer end (Dct) from the outer end (Dct) and a base end (Dcb) in an axial direction (Dc) along the axis (Ac) inside the cylinder (50X), wherein the fuel nozzle (60) of the combustion chamber cylinder (50) is a secondary fuel nozzle capable of injecting secondary fuel (F2). A gas turbine (10) comprising: the combustion chamber (40) according to claim 10, a compressor (20) capable of generating compressed air (Acom) used for the combustion of fuel (F) inside the cylinder (50X) by compressing air (A), and a turbine (30) that can be driven by means of combustion gas (G) generated by the combustion of fuel (F) inside the cylinder (50X).

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