Cylinder for combustion chamber, combustion chamber and gas turbine

Abstract

Cylinder (12) for a combustion chamber through which a combustion gas flows during operation and which is configured to supply the combustion gas (Cg) to a turbine (3), wherein the cylinder (12) for a combustion chamber comprises the following: a cylindrical element (21) extending along an axis, a first cooling channel (22) which is formed in an upstream region (21A) which is located upstream in a flow direction of the combustion gas (Cg) of a wall section of the cylindrical element (12), wherein the first cooling channel (22) comprises a supply opening (25,25A) which opens to an outer circumferential surface (21c) of the cylindrical element (21) and is configured to cool the upstream region (21A) via a first cooling fluid (Ca) which is supplied via the supply opening (25,25A) from a space (10A) outside the cylindrical element (21), a second cooling channel (23) which is formed in a downstream region (21B) located downstream in the direction of flow of the combustion gas (Cg) of the wall section of the cylindrical element (21) next to the upstream region (21A), wherein the second cooling channel (23) is configured to cool the downstream region (21B) by means of supplied second cooling fluid, and has an outlet opening (27) which opens to the outer circumferential surface (21c) of the cylindrical element (21) downstream of the supply opening (25,25A) in the flow direction of the combustion gas (Cg) and is configured to discharge the second cooling fluid into the space (10A) outside the cylindrical element (21), and a supply opening extension section (30) comprising the following: a first wall section (31) which is arranged between the supply opening (25,25A) and the outlet opening (27) extending in a direction away from the outer circumferential surface (21c) of the cylindrical element (21), a second wall section (32) which is arranged upstream of the supply opening (25,25A) in the flow direction of the combustion gas (Cg), wherein the second wall section (32) extends in a direction away from the outer circumferential surface (21c) of the cylindrical element (21), and a guide channel (33) formed between the first wall section (31) and the second wall section (32), wherein the guide channel (33) is configured to direct the first cooling fluid (Ca) from the space (10A) outside the cylindrical element (21) to the supply opening (25,25A).

Description

[0001] The present invention relates to a cylinder for a combustion chamber, a combustion chamber and a gas turbine.

[0002] A gas turbine combustion chamber is equipped with a transition piece configured to supply high-temperature combustion gas to the turbine. JP 2012-077 660 A describes a structure in which two types of cooling channels are formed in a wall section of the transition piece to cool that wall section. The first cooling channel is formed in an upstream region of the transition piece, located on the upstream side in the direction of flow of the combustion gas passing through the transition piece. In the first cooling channel, air from an interior space of the gas turbine casing, where the transition piece is located, is supplied to the upstream region of the transition piece as the first cooling air. Accordingly, the first cooling channel includes a supply opening that opens to the outer circumferential surface of the transition piece to supply the first cooling air.

[0003] The second cooling channel is formed in a downstream section of the transition piece, located opposite the previously described upstream side in the direction of combustion gas flow. A portion of compressed air, generated in a compressor of the gas turbine, is fed into the downstream section of the transition piece as a second cooling air stream. After being supplied to the second cooling channel to cool the downstream section, this second cooling air is discharged into the interior of the gas turbine casing, where the transition piece is located. Accordingly, the second cooling channel has an outlet opening that faces the outer surface of the transition piece to release the second cooling air into the casing interior.The outlet of the second cooling channel is located downstream of the supply opening of the first cooling channel in the direction of combustion gas flow. The air exiting the outlet is the second cooling air, which is heated by the cooling of the transition piece, resulting in high-temperature air.

[0004] JP 2012-077 660 A also describes the provision of a partition located between the supply port of the first cooling channel and the outlet port of the second cooling channel. The partition projects from the outer circumferential surface of the transition piece and is configured to prevent the high-temperature air, which is discharged from the outlet port of the second cooling channel into the housing interior, from entering the first cooling channel from the supply port.

[0005] US Patent 2010 / 0170260A1 discloses a gas turbine with a combustion chamber cylinder and a transition piece downstream of it. The wall of the combustion chamber cylinder is cooled in an upstream region (relative to the flow direction of the combustion gas in the combustion chamber cylinder) by a number of internal cooling air channels and in a downstream region by a number of internal steam channels. Compressed air is introduced into the upstream internal cooling air channels in the gas turbine casing outside the combustion chamber cylinder via supply openings. The steam used to cool the downstream region is contained in a closed system and introduced into the internal steam channels via a downstream steam jacket and discharged again via an upstream steam jacket.

[0006] US Patent 2005 / 0097890A1 discloses a gas turbine combustion chamber in which a combustion chamber cylinder has internal cooling air channels and external damping chambers. Compressed air is introduced into the internal cooling air channels in the gas turbine casing outside the combustion chamber cylinder via supply openings.

[0007] From US Patent 2013 / 0333388A1, a combustion chamber lining cooling arrangement for a gas turbine system is known, comprising a combustion chamber lining that defines a combustion chamber. A flow sleeve surrounds at least a portion of the combustion chamber lining, the flow sleeve having at least one row of openings with a plurality of openings, each of which directs a cooling stream onto the combustion chamber lining. Furthermore, a plurality of flow-deflectoring components are included, arranged near a downstream end of the flow sleeve, the plurality of flow-deflectoring components deflecting an impact crossflow that flows relatively perpendicular to the cooling stream, thereby providing the cooling stream with an undisturbed flow path to the combustion chamber lining.

[0008] In the housing interior where the transition piece is located, the combustion gas can flow in the transition piece in the opposite direction to the flow direction, and the high-temperature air exiting the outlet of the second cooling channel can flow upstream of the supply opening in the direction of combustion gas flow. In this case, the high-temperature air outlet from the supply opening enters the first cooling channel, making it difficult to sufficiently reduce the temperature of the air entering the first cooling channel. Cooling of the upstream portion of the transition piece may be inadequate.

[0009] An objective of the present invention is to provide a cylinder for a combustion chamber which offers improved cooling effect and more reliable prevention of high-temperature air which is released from the second cooling channel and fed into the first cooling channel, and a combustion chamber and a gas turbine which is provided with the same.

[0010] The present invention relates to a cylinder for a combustion chamber with the features of claim 1, through which a combustion gas flows during operation and which is configured to direct the combustion gas to the turbine. The cylinder for a combustion chamber comprises a cylindrical element extending along an axis. The cylinder for a combustion chamber further comprises a first cooling channel formed in an upstream region located upstream of a wall section of the cylindrical element in the direction of combustion gas flow, wherein the first cooling channel includes a supply opening that opens to an outer circumferential surface of the cylindrical element and is configured to cool the upstream region via a first cooling fluid supplied from a space outside the cylindrical element through the supply opening.The cylinder for a combustion chamber further comprises a second cooling channel formed in a downstream region located downstream of the wall section of the cylindrical element next to the upstream region in the direction of flow of the combustion gas, wherein the second cooling channel is configured to cool the downstream region by means of supplied cooling fluid and has an outlet opening that opens to the outer circumferential surface of the cylindrical element in the direction of flow of the combustion gas and is configured to discharge the second cooling fluid into the space outside the cylindrical element.The cylinder for a combustion chamber further comprises a supply opening extension section, comprising a first wall section extending between the supply opening and the outlet opening in a direction away from the outer circumferential surface of the cylindrical element, and a second wall section extending upstream of the supply opening in the direction of flow of the combustion gas, the second wall section extending in a direction away from the outer circumferential surface of the cylindrical element.

[0011] In the cylinder described above for a combustion chamber, the first wall section of the supply port extension section is located between the supply port and the outlet port. Consequently, even when fluid, part of which serves as the first cooling fluid, flows in the opposite direction to the combustion gas flow within the cylindrical element, the first wall section prevents high-temperature fluid (the second cooling air, heated by cooling the wall section of the cylindrical element) exiting the outlet port of the second cooling channel from entering the first cooling channel from the downstream supply port.

[0012] The previously described cylinder for a combustion chamber is designed with the second wall section of the supply port extension section positioned upstream of the supply port in the direction of combustion gas flow. Even though the high-temperature fluid discharged from the outlet port consequently flows upstream of the supply port in the direction of combustion gas flow into the space outside the cylindrical element, the second wall section prevents the high-temperature fluid from approaching the supply port. Accordingly, it prevents the high-temperature fluid, after flowing upstream of the supply port in the direction of combustion gas flow, from entering the first cooling channel from the supply port.

[0013] In the previously described cylinder for a combustion chamber, the supply port extension section, with its first and second wall sections, opens to the space outside the cylindrical element at a position spaced from the outer circumferential surface of the cylindrical element. This area, spaced from the outer circumferential surface of the cylindrical element, is difficult for the high-temperature fluid exiting from the outlet port to reach. Consequently, the low-temperature fluid present in this area can enter the first cooling channel as the primary cooling fluid. Therefore, the upstream region of the cylindrical element can be efficiently cooled.

[0014] According to the present invention, the cylinder for a combustion chamber further comprises a guide channel formed between the first wall section and the second wall section, the guide channel being configured to direct the first cooling fluid from the space outside the cylindrical element to the supply opening. Preferably, the guide channel includes an opening section to the space outside the cylindrical element, which is directed outwards in a radial direction of the cylindrical element.

[0015] Alternatively, the guide channel preferably comprises an opening section to the space outside the cylindrical element, which points downstream in the direction of flow of the combustion gas and is located downstream of the outlet opening in the direction of flow of the combustion gas.

[0016] Preferably, the first wall section and the second wall section are formed in a circumferential direction around an entirety of the cylindrical element to form an annular channel section that is connected to the supply opening.

[0017] Preferably, the cylinder for a combustion chamber further comprises a pair of prevention sections configured to prevent the first cooling fluid from entering the annular channel section from the space outside the cylindrical element, the pair of prevention sections being arranged at opposite positions in the radial direction of the cylindrical element.

[0018] Preferably, the cylinder for a combustion chamber further comprises a separating section that divides the annular channel section in the circumferential direction.

[0019] Preferably, a pair of the separating sections is arranged at opposite positions in the radial direction of the cylindrical element.

[0020] Preferably, the channel cross-section of the annular channel section perpendicular to the circumferential direction of the cylindrical element is equal to or greater than 50 times the opening area of ​​the supply opening.

[0021] Preferably, the first wall section and the second wall section are formed in a cylindrical shape to form a cylindrical channel section that communicates with the annular channel section and the space outside the cylindrical element.

[0022] Preferably, a plurality of the cylindrical channel sections are arranged at intervals in the circumferential direction of the cylindrical element.

[0023] Preferably, a plurality of the supply openings are arranged at intervals in a circumferential direction of the cylindrical element, and a plurality of the first wall sections and the second wall sections are formed in cylindrical shapes to form a plurality of cylindrical channel sections, which are formed at intervals in the circumferential direction of the cylindrical element, wherein each of the plurality of cylindrical channel sections is connected to one of the plurality of supply openings.

[0024] Preferably, positions in the circumferential direction of the plurality of cylindrical channel sections are aligned with positions in the circumferential direction of centers of a plurality of burners, which are provided on an end section of the cylindrical element that is located upstream in the flow direction of the combustion gas and are arranged in the circumferential direction of the cylindrical element.

[0025] Preferably, the majority of cylindrical channel sections are arranged at equal intervals in the circumferential direction of the cylindrical element.

[0026] Preferably, the supply opening extension section is provided with a connecting section that is connected to a first space of the space outside the cylindrical element, which is located downstream of the first wall section in the direction of flow of the combustion gas, and to a second space of the space outside the cylindrical element, which is located upstream of the second wall section in the direction of flow of the combustion gas.

[0027] Preferably, the supply opening extension section is provided with a thermal insulation layer configured to reduce heat conduction at the first wall section and the second wall section.

[0028] Preferably, the supply opening extension section is supported by the outer circumferential surface of the cylindrical element.

[0029] Preferably, the cylinder for a combustion chamber comprises an acoustic lining which is arranged upstream of the supply opening extension section of the cylindrical element in the flow direction of the combustion gas, wherein the supply opening extension section is supported by the acoustic lining.

[0030] Preferably, the supply opening extension section is formed integrally with the cylindrical element.

[0031] The present invention also relates to a combustion chamber with the features of claim 19, which is provided with the cylinder for a combustion chamber according to the invention and has a burner configured to inject fuel.

[0032] The present invention further relates to a gas turbine with the features of claim 20, which is provided with the combustion chamber according to the invention, a compressor configured to generate compressed air to be supplied to the combustion chamber, and a turbine with a rotor configured to be rotated by the combustion gas supplied from the combustion chamber.

[0033] According to the cylinder for a combustion chamber, the combustion chamber, and the gas turbine described above, it is possible to more reliably prevent high-temperature fluid (the second cooling fluid, which is heated by cooling the wall section of the cylindrical element) exiting the outlet of the second cooling channel from entering the first cooling channel. This allows the upstream region of the cylindrical element to be efficiently cooled by the first cooling fluid entering the first cooling channel. In other words, the cooling effect of the cylinder for a combustion chamber can be improved. Fig. Figure 1 is a schematic representation of the entire configuration of a gas turbine according to a first embodiment of the present invention. Fig. Figure 2 is a view of an example of the configuration of the gas turbine according to the first embodiment and circumferential structures. Fig. Figure 3 is a schematic cross-sectional view of a cylinder for a combustion chamber according to the first embodiment of the present invention. Fig. Figure 4 is a cross-sectional view of the main components of the cylinder for a combustion chamber located in Fig. 3 is shown. Fig. Figure 5 is a top view from the outside in the radial direction of a transition piece of the main components of the cylinder for a combustion chamber, which is in Fig. 4 is shown. Fig. Figure 6 is a partially fragmented perspective view of the main components of the cylinder for a combustion chamber, which is in Fig. 4 and Fig. 5 is shown. Fig. Figure 7 is a schematic cross-sectional view from upstream in a flow direction of a combustion gas of a cylinder for a combustion chamber according to a second embodiment of the present invention. Fig. Figure 8 is an enlarged cross-sectional view of the main components of the cylinder for a combustion chamber located in Fig. 7 is shown. Fig. Figure 9 is a cross-sectional view of the main components of a cylinder for a combustion chamber according to a third embodiment of the present invention. Fig. Figure 10 is a cross-sectional view of the main components of a cylinder for a combustion chamber according to a fourth embodiment of the present invention. Fig. Figure 11 is a cross-sectional view of the main components of a cylinder for a combustion chamber according to a fifth embodiment of the present invention. Fig. Figure 12 is a top view from the outside in the radial direction of a transition piece of the main components of the cylinder for a combustion chamber, which is in Fig. 11 is shown. Fig. Figure 13 is a cross-sectional view of the main components of a first example of a cylinder for a combustion chamber according to a sixth embodiment of the present invention. Fig. Figure 14 is a cross-sectional view, taken along AA in the direction of the arrow in Fig. 13. Fig. Figure 15 is a cross-sectional view of the main components of a second example of the cylinder for a combustion chamber according to the sixth embodiment of the present invention. Fig. Figure 16 is a cross-sectional view of the main components of a cylinder for a combustion chamber according to a seventh embodiment of the present invention. Fig. Figure 17 is a schematic cross-sectional view from upstream in a flow direction of a combustion gas of a cylinder for a combustion chamber according to an eighth embodiment of the present invention. Fig. 18 is a view, made along CC in Fig. 17 in the direction of the arrow. Fig. Figure 19 is a graph showing the circumferential flow velocity distribution near the circumference of the transition piece located in Fig. 17 is shown. Fig. Figure 20 is a graph showing the static pressure distribution in the circumferential direction near the circumference of the transition piece located in Fig. 17 is shown. Fig. Figure 21 is a schematic cross-sectional view from upstream in a flow direction of a combustion gas of a cylinder for a combustion chamber according to a ninth embodiment of the present invention. Fig. Figure 22 is a top view of the main components of a non-inventive first example of a cylinder for a combustion chamber. Fig. Figure 23 is a top view of the main components of a non-inventive second example of a cylinder for a combustion chamber. Fig. Figure 24 is a cross-sectional view of the main components of a cylinder for a combustion chamber according to another embodiment of the present invention. Fig. 25 is a cross-sectional view, taken along EE in Fig. 24 in the direction of the arrow.

[0034] Embodiments of a cylinder for a combustion chamber, a combustion chamber, and a gas turbine according to the present invention are described below with reference to the drawings. However, the present invention is not limited to these embodiments.

[0035] First, a cylinder for a combustion chamber, a combustion chamber and a gas turbine is selected according to a first embodiment with reference to Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 to Fig. 6 described.

[0036] As in Fig. Figure 1 shows a gas turbine GT of the present embodiment with a compressor 1, a combustion chamber 2 and a turbine 3.

[0037] Compressor 1 draws in air from an air inlet opening as a working fluid and generates compressed air.

[0038] Combustion chamber 2 is connected to an outlet opening of compressor 1. Combustion chamber 2 injects fuel into the compressed air released by compressor 1 to produce a combustion gas with a high temperature and high pressure.

[0039] Turbine 3 converts the thermal energy of the combustion gas, which is fed in from combustion chamber 2, into rotational energy for a rotor 4, thus generating a driving force. Turbine 3 transmits the generated driving force to a generator Ge, which is connected to the rotor 4.

[0040] The gas turbine GT of the present embodiment is further equipped with a pressurization device 5. The pressurization device 5 draws off a portion of the compressed air at the compressor 1 in order to pressurize the compressed air to a higher pressure. The pressurization device 5 is provided on a branch channel 7 and is driven, for example, by an electric motor M. The branch channel 7 branches off from a compressed air supply channel 6, through which compressed air is supplied from the compressor 1 to the combustion chamber 2, and draws off a portion of the compressed air. The drawn-off pressurized air, which is pressurized in the pressurization device 5, is fed into the combustion chamber 2 through a channel of the pressurized air 8 and is used as air (hereinafter referred to as "cooling air") for cooling a transition piece 21 of the combustion chamber 2, as described below.After being used to cool the transition piece 21, the cooling air is returned to the compressed air supply channel 6 via a return channel 9, where the returned cooling air merges with the main flow of compressed air flowing through compressed air supply channel 6. The cooling air is then reused as combustion air for the combustion of fuel in the combustion chamber 2.

[0041] In other words, the GT gas turbine of the present embodiment is provided with an air cooling structure with recovery (closed-loop cooling structure) in which a portion of the compressed air supplied by compressor 1 and used as combustion air in combustion chamber 2 is used as cooling air to cool the transition piece 21 of combustion chamber 2. This cooling air is then recovered and reused as combustion air in combustion chamber 2 together with the main flow of compressed air. The use of the portion of compressed air drawn from the main flow (compressed air supply channel 6) is not limited to cooling the transition piece 21 of combustion chamber 2, as described in [reference missing]. Fig. 1 shown, and it can be used, for example, next to the transition piece 21 of the combustion chamber 2 for cooling the wings and blades of the turbine 3.

[0042] Combustion chamber 2 has an essentially cylindrical exterior and is, as in Fig. The combustion chamber 2 is arranged primarily within a housing interior 10A, which is formed within a housing 10 of the gas turbine GT. Compressed air, pressurized by the compressor 1, is fed into the housing interior 10A, where the combustion chamber 2 is located, to fill the housing interior 10A. The combustion chamber 2 is provided with a combustion chamber main body 11 and a cylinder for a combustion chamber 12.

[0043] The combustion chamber main body 11 serves as a combustion chamber, causing the supplied fuel to react with the compressed air released by the compressor 1. The cylinder for a combustion chamber 12 directs the combustion gas flowing from the combustion chamber main body 11 to the turbine 3.

[0044] The combustion chamber main body 11 is provided with a substantially cylindrical combustion chamber basket 13 and a burner 14, which is provided in the combustion chamber basket 13, which injects the fuel.

[0045] A first opening of the combustion chamber basket 13 is an upstream opening for supplying compressed air, which is filled into the housing interior 10A, into the combustion chamber basket 13. A second opening of the combustion chamber basket 13 is a downstream opening, which is connected to the transition piece 21 described below. The burner 14 comprises a pilot burner 15 and a main burner 16. The pilot burner 15 is arranged along the central axis of the combustion chamber basket 13. The pilot burner 15 injects fuel supplied from the outside to induce diffusion combustion of the fuel. A plurality of main burners 16 are provided in the combustion chamber basket 13. The plurality of main burners 16 are arranged at intervals around the pilot burner 15 in the circumferential direction of the combustion chamber basket 13. Each main burner 16 extends parallel to the central axis of the combustion chamber basket 13.The main burners 16 inject a fuel-air premixture, which is created by pre-mixing injected fuel and compressed air. This fuel-air mixture is then burned.

[0046] The cylinder for a combustion chamber 12 is, as in Fig. 2, Fig. 3, Fig. 4, Fig. 5 to Fig. 6 shown, with a transition piece (cylindrical element) 21, a first cooling channel 22, a second cooling channel 23 and an acoustic lining 24.

[0047] The transition piece 21 extends along the axis. Furthermore, the transition piece 21 increases the flow velocity of the combustion gas Cg, which flows in from the combustion chamber main body 11, and directs the combustion gas Cg to the turbine 3. A first opening of the transition piece 21 is connected to a downstream opening of the combustion chamber basket 13 of the combustion chamber main body 11 described above (see Fig. 2) A second opening of the transition piece 21 is connected to the turbine 3. The combustion gas Cg, which flows in from the combustion chamber main body 11, flows through the interior of the transition piece 21. In Fig. 3, Fig. 4, Fig. 5 to Fig. 6. The combustion gas Cg flows through the interior of the transition piece 21 from the left side (upstream side) to the right side (downstream side) of the paper. In the space around the outside of the transition piece 21, i.e., in the housing interior 10A, the compressed air Ca, which is released by the compressor 1, flows towards the upstream opening of the combustion chamber basket 13 described above, in the opposite direction to the flow direction of the combustion gas Cg in the transition piece 21.

[0048] The first cooling channel 22 is formed in an upstream region 21A, which is located upstream in the flow direction of the combustion gas Cg, of the wall section of the transition piece 21. The first cooling channel 22 includes a supply opening 25 that opens onto an outer circumferential surface 21c of the transition piece 21. Accordingly, the first cooling channel 22 supplies the compressed air (fluid) Ca from the housing interior 10A via the supply opening 25 as the first cooling air (first cooling fluid) to cool the upstream region 21A of the transition piece 21.

[0049] The first cooling channel 22 of the present embodiment extends along the axial direction of the transition piece 21. A plurality of the first cooling channels 22 are arranged at intervals in the circumferential direction of the transition piece 21.

[0050] For each of the first cooling channels 22, a supply opening 25 is provided on each side in the direction of flow of the combustion gas Cg of the acoustic lining 24, which is located in the upstream region 21A of the transition piece 21. The supply openings 25A (hereinafter referred to as downstream supply openings 25A) of the majority of first cooling channels 22, which are located downstream of the acoustic lining 24 in the direction of flow of the combustion gas Cg, are aligned in the circumferential direction of the transition piece 21. Each of the first cooling channels 22 has an outlet opening 26 that opens towards the outer circumferential surface 21c of the transition piece 21 and discharges the first cooling air outside the transition piece 21. The outlet openings 26 of the first cooling channels 22 open towards the inside of the acoustic lining 24.In other words, the cooling air is released into the interior of the acoustic lining 24 after cooling the upstream area 21A of the transition piece 21.

[0051] The second cooling channel 23 is formed in a downstream section 21B, which is located downstream of the upstream section 21A of the transition piece 21 in the direction of flow of the combustion gas Cg, within the wall section of the transition piece 21. The second cooling channel 23 carries the vented pressurized air, which is pressurized in the pressure device 5 described above (see Fig. 1) The second cooling channel 23 supplies a second cooling air (second cooling fluid) to cool the downstream area 21B of the transition piece 21. The second cooling channel 23 includes an outlet opening 27, which opens towards the outer circumferential surface 21c of the transition piece 21 downstream of the downstream supply opening 25A. The outlet opening 27 releases the second cooling air into the housing interior 10A.

[0052] The second cooling channel 23 of the present embodiment extends along the axial direction of the transition piece 21. A plurality of the second cooling channels 23 are arranged at intervals in the circumferential direction of the transition piece 21.

[0053] The outlet openings 27 of the second cooling channels 23 are provided at the first end sections in the longitudinal direction of the second cooling channels 23, which are located upstream in the flow direction of the combustion gas Cg. The outlet openings 27 of the second cooling channels 23 are arranged in the circumferential direction of the transition piece 21.

[0054] Each of the second cooling channels 23 includes a supply opening 28 that opens towards the outer circumferential surface 21c of the transition piece 21 to supply the second cooling air to the second cooling channel 23. The supply openings 28 of the second cooling channels 23 are provided at second end sections in the longitudinal direction of the second cooling channels 23 and are located in the downstream end section of the transition piece 21 on the turbine 3 side.

[0055] An annular channel section 29 (distributor) is formed on the outer circumferential surface 21c of the transition piece 21 at the downstream end section, extending circumferentially around the entire transition piece 21. The annular channel section 29 encompasses the supply openings 28 of the majority of secondary cooling channels 23 as a whole and defines an inlet space that communicates with the supply openings 28 of the secondary cooling channels 23. The annular channel section 29 is designed such that the inlet space does not communicate with the interior of the housing 10A. Accordingly, the secondary cooling air (vented pressurized air, which is pressurized in the pressure device 5) is supplied from the supply openings 28 of the secondary cooling channels 23 to the secondary cooling channels 23 via the interior of the annular channel section 29.

[0056] The second cooling air, supplied to the second cooling channels 23, is discharged into the housing interior 10A after cooling the downstream section 21B of the transition piece 21. The second cooling air in the second cooling channels 23 is heated by cooling the wall section of the transition piece 21. Upon discharge from the outlet openings 27 of the second cooling channels 23, the second cooling air consequently becomes high-temperature air (high-temperature fluid) with a temperature higher than the temperature of the second cooling air at the supply openings 28 of the second cooling channels 23 and the temperature of the compressed air Ca contained in the housing interior 10A. The high-temperature air (second cooling air) discharged into the housing interior 10A mixes with the compressed air Ca contained in the housing interior 10A and is reused as combustion air.

[0057] The acoustic lining 24 is provided on the circumference of the transition piece 21 in the upstream region 21A. Part of the acoustic lining 24 is formed by the wall section of the transition piece 21. The space in the acoustic lining 24 communicates with the interior of the transition piece 21 via a plurality of acoustic holes 24A, which are formed by passing through the wall section of the transition piece 21. Accordingly, the first cooling channel 22 described above is located in a position that does not interfere with the acoustic holes 24A. The acoustic lining 24 reduces combustion vibrations of the gas turbine GT (natural vibrations caused by resonance of pressure fluctuations, flow velocity fluctuations, and fluctuations in the heat dissipation rate in the combustion chamber 2).

[0058] By providing the acoustic holes 24A in the acoustic lining 24, as previously described, the first cooling air released from the outlet opening 26 of the first cooling channel 22 described above in the acoustic lining 24 flows through the acoustic holes 24A into the interior of the transition piece 21.

[0059] The cylinder described above for a combustion chamber 12 is equipped with a supply opening extension section 30, as shown in Fig. 4, Fig. 5 to Fig. 6 shown, provided.

[0060] The supply opening extension section 30 is provided with a first wall section 31 between the downstream supply opening 25A of the first cooling channel 22 and the outlet opening 27 of the second cooling channel 23. The first wall section 31 extends in a direction away from the outer circumferential surface 21c of the transition piece 21. The supply opening extension section 30 is further provided with a second wall section 32 in the flow direction of the combustion gas Cg upstream of the downstream supply opening 25A. The second wall section 32 extends in a direction away from the outer circumferential surface 21c of the transition piece 21. In the present embodiment, the second wall section 32 is arranged between the downstream supply opening 25A of the first cooling channel 22 and the acoustic lining 24.

[0061] A guide channel 33 is formed between the first wall section 31 and the second wall section 32. The guide channel 33 directs the compressed air Ca, which becomes the first cooling air, from the housing interior 10A to the downstream supply opening 25A of the first cooling channel 22. An opening section 33A of the guide channel 33 to the housing interior 10A is located at least a distance from the outer circumferential surface 21c of the transition piece 21, extending outwards in the radial direction of the transition piece 21. In the present embodiment, the opening section 33A of the guide channel 33 faces outwards in the radial direction of the transition piece 21. In other words, in the present embodiment, the first wall section 31 and the second wall section 32 extend outwards in the radial direction of the transition piece 21.

[0062] The vertical position of the opening section 33A of the guide channel 33 relative to the outer circumferential surface 21c of the transition piece 21 is not limited to any specific vertical position and can, for example, be Fig. 4 shown, set lower than the acoustic lining 24 or set higher than the acoustic lining 24.

[0063] In the present embodiment, the first wall section 31 and the second wall section 32 are formed circumferentially around the entire transition piece 21 to form an annular channel section 34 that communicates with the downstream supply opening 25A. Furthermore, the first wall section 31 and the second wall section 32 are formed in a cylindrical shape and form a cylindrical channel section 35 that communicates with the annular channel section 34 and the housing interior 10A.

[0064] In other words, the sections of the annular channel section 34 and the cylindrical channel section 35 located downstream of the downstream supply opening 25A in the direction of flow of the combustion gas Cg are formed by the first wall section 31. The sections of the annular channel section 34 and the cylindrical channel section 35 located upstream of the downstream supply opening 25A in the direction of flow of the combustion gas Cg are formed by the second wall section 32.

[0065] The guide channel 33 described above is formed by the first channel section 34 and the cylindrical channel section 35. The opening of the cylindrical channel section 35 in the housing interior 10A corresponds to the opening section 33A of the guide channel 33. The cylindrical channel section 35 of the present embodiment extends straight in the radial direction of the transition piece 21. Accordingly, the opening section 33A of the guide channel 33 faces outwards in the radial direction of the transition piece 21.

[0066] The supply opening extension section 30 of the present embodiment is provided with a connecting section 36, which is connected to a first chamber 10A1 and a second chamber 10A2 of the housing interior 10A. The first chamber 10A1 is located downstream of the first wall section 31 in the direction of flow of the combustion gas Cg, and the second chamber 10A2 is located upstream of the second wall section 32 in the direction of flow of the combustion gas Cg. In the present embodiment, a plurality of the cylindrical channel sections 35 are arranged at intervals in the circumferential direction of the transition piece 21. This allows each of the spaces between adjacent cylindrical channel sections 35 to serve as the connecting section 36 described above.

[0067] The circumferential positions of the cylindrical channel sections 35, which are arranged in the circumferential direction of the transition piece 21, can be aligned with the circumferential positions of the downstream supply openings 25A, which are arranged in the circumferential direction of the transition piece 21, as for example in Fig. 5 shown, are arranged. But the positions in the circumferential direction of the cylindrical channel sections 35 can also be offset in the circumferential direction of the transition piece 21 with the position in the circumferential direction of the downstream supply openings 25A.

[0068] Each of the cylindrical channel sections 35 can be located above a downstream supply opening 25A in the radial direction of the transition piece 21, as for example in Fig. 5 shown, provided for. However, each of the cylindrical channel sections 35 can, for example, also be located above a plurality of the downstream supply openings 25A in the radial direction of the transition piece 21. Each individual cylindrical channel section 35 need not, for example, be located above a downstream supply opening 25A in the radial direction of the transition piece 21.

[0069] Each of the cylindrical channel sections 35 can, when viewed from the outside, have a circular cylindrical shape in the radial direction of the transition piece 21, as shown in Fig. 5 shown. The shape can, for example, also be a square cylindrical shape or an elliptical or rectangular cylindrical shape extending in the circumferential direction of the transition piece 21.

[0070] The supply opening extension section 30 of the present embodiment is supported by the outer circumferential surface 21c of the transition piece 21. In particular, the supply opening extension section 30 is attached to the outer circumferential surface 21c of the transition piece 21, for example, by welding, soldering, or the like. Fig. 4, Fig. 5 to Fig. 6 the annular channel section 34 of the extension section of the supply opening 30 is attached to the outer circumferential surface 21c of the transition piece 21.

[0071] The provision of the above-described extension section of the supply opening 30 is not limited to the downstream supply opening 25A of the first cooling channel 22 and can, for example, be provided on both supply openings 25 of the first cooling channels 22.

[0072] The cylinder for a combustion chamber 12 of the present embodiment, which is formed as described above, is provided with the first wall section 31 of the extension section of the supply opening 30 between the downstream supply opening 25A of the first cooling channel 22 and the outlet opening 27 of the second cooling channel 23. Even when compressed air Ca flows into the housing interior 10A in the opposite direction to the flow direction of the combustion gas Cg in the transition piece 21, the first wall section 31 can therefore prevent high-temperature air (the second cooling air, which is heated by cooling the wall section of the transition piece 21), which is released from the outlet opening 27 of the second cooling channel 23, from entering the first cooling channel 22 from the downstream supply opening 25A.

[0073] The cylinder for a combustion chamber 12 of the present embodiment is provided with the second wall section 32 of the extension section of the supply opening 30 upstream of the downstream supply opening 25A of the first cooling channel 22 in the flow direction of the combustion gas Cg. Even if the high-temperature air (second cooling air), which is released from the outlet opening 27 of the second cooling channel 23, consequently flows upstream from the downstream supply opening 25A of the first cooling channel 22 in the flow direction of the combustion gas Cg due to the flow of the compressed air Ca in the housing interior 10A, the second wall section 32 can prevent the high-temperature air from approaching the downstream supply opening 25A.Accordingly, it can be prevented that the high-temperature air, after flowing upstream from the downstream supply opening 25A in the direction of flow of the combustion gas Cg, enters the first cooling channel 22 from the downstream supply opening 25A.

[0074] In the cylinder for a combustion chamber 12 of the present embodiment, the supply opening extension section 30, consisting of the first wall section 31 and the second wall section 32, opens to the housing interior 10A at a position spaced apart from the outer circumferential surface 21c of the transition piece 21. The area spaced apart from the outer circumferential surface 21c of the transition piece 21 is difficult for the high-temperature air exiting from the outlet opening 27 of the second cooling channel 23 to reach. Consequently, the compressed air Ca, whose temperature is lower than that of the high-temperature air present in the area spaced apart from the outer circumferential surface 21c of the transition piece 21, can enter the first cooling channel 22 as the first cooling fluid.

[0075] According to the cylinder for a combustion chamber 12 and the combustion chamber 2 and gas turbine GT provided with it, in accordance with the embodiment described above, it is possible to more reliably prevent the high-temperature air, which is discharged from the outlet opening 27 of the second cooling channel 23, from entering the first cooling channel 22, and the upstream region 21A of the transition piece 21 can be cooled more efficiently by the first low-temperature cooling fluid, which is fed into the first cooling channel 22. In other words, the cooling effect of the cylinder for a combustion chamber 12 can be improved.

[0076] According to the cylinder for a combustion chamber 12 of the present embodiment, the opening section 33A of the guide channel 33 of the extension section of the supply opening 30, which is spaced apart from the outer circumferential surface 21c of the transition piece 21, faces outwards in the radial direction of the transition piece 21. Consequently, it is thus possible to prevent high-temperature air (second cooling air), which is released from the outlet opening 27 of the second cooling channel 23, which opens towards the outer circumferential surface 21c of the transition piece 21, from entering the guide channel 33.

[0077] The structure of the cylinder for a combustion chamber 12 of the present embodiment, in which the opening section 33A of the guide channel 33 faces outwards in the radial direction of the transition piece 21, can be manufactured easily. For example, the straight cylindrical channel section 34 and the cylindrical channel section 35 can be manufactured easily, and the annular channel section 34 and the cylindrical channel section 35 are simply installed to extend outwards in the radial direction of the transition piece 21. In other words, the manufacture and installation of the extension section of the supply opening 30 can be carried out simply. Accordingly, the cylinder for a combustion chamber 12, which is provided with the supply opening extension section 30, can be manufactured cost-effectively.

[0078] According to the cylinder for a combustion chamber 12 of the present embodiment, the supply opening extension section 30 is formed by the annular channel section 34 and the cylindrical channel section 35, which are built upon one another on the outer circumferential surface 21c of the transition piece 21. The opening section 33A of the guide channel 33 is configured by the cylindrical channel section 35. In other words, the area of ​​the opening section 33A through which the compressed air Ca is fed into the guide channel 33 is defined as the cylindrical channel section 35. Therefore, it can be appropriately prevented that high-temperature air (secondary cooling air), which is released from the outlet opening 27 of the second cooling channel 23, enters the guide channel 33.

[0079] In the cylinder for a combustion chamber 12 of the present embodiment, the compressed air Ca (first cooling air), which is fed from the housing interior 10A into the space within the cylindrical channel section 35, is fed into the space within the annular channel section 34 in order to disperse around the entire transition piece 21 in the circumferential direction. Therefore, even if the cylindrical channel section 35 is provided in only one region of the transition piece 21 in the circumferential direction, the compressed air Ca can be supplied to the plurality of first cooling channels 22, which are arranged around the circumference.

[0080] According to the cylinder for a combustion chamber 12 of the present embodiment, the supply opening extension section 30 is provided with the connecting section 36, which is connected to a first chamber 10A1 and a second chamber 10A2 of the housing interior 10A. The first chamber 10A1 is located downstream of the first wall section 31 in the direction of flow of the combustion gas Cg, and the second chamber 10A2 is located upstream of the second wall section 32 in the direction of flow of the combustion gas Cg. Consequently, the high-temperature air, which is discharged from the outlet opening 27 of the second cooling channel 23, is mixed with the flow of compressed air Ca in the housing interior 10A and flows from the first chamber 10A1 to the second chamber 10A2 via the connecting section 36. This prevents the high-temperature air from flowing outwards in a radial direction.Therefore, the length of the first wall section 31 and the second wall section 32, which extend in the radial direction from the outer circumferential surface 21c of the transition piece 21, can be limited to a short length.

[0081] In the cylinder for a combustion chamber 12 of the present embodiment, the connecting section 36 of the extension section of the supply opening 30 is formed from a free space between the cylindrical channel sections 35 adjacent in the circumferential direction. Since the straight-extending cylindrical channel section 35, as described above, can be easily manufactured, the connecting section 36 of the extension section of the supply opening 30 can also be easily manufactured.

[0082] According to the cylinder for a combustion chamber 12 of the present embodiment, the supply opening extension section 30 is attached to the outer circumferential surface 21c of the transition piece 21 by welding. Consequently, the formation of gaps between the supply opening extension section 30 and the outer circumferential surface 21c of the transition piece 21 can be reliably prevented. Therefore, it can be prevented that the compressed air Ca, which is supplied from the housing interior 10A to the guide channel 33 of the extension section of the supply opening 30, escapes from the gap between the supply opening extension section 30 and the outer circumferential surface 21c of the transition piece 21 into the housing interior 10A, and the compressed air Ca can be efficiently fed into the first cooling channel 22.

[0083] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a second embodiment according to the present invention with reference to Fig. 7 and Fig. 8 described. In the second embodiment, components that are identical to those of the first embodiment described above have the same reference symbols in the drawings, and explanations thereof are omitted.

[0084] As in Fig. 7 and Fig. As shown in Figure 8, the combustion chamber 2 of the present embodiment is connected to the combustion chamber main body 11 (see Figure 8). Fig. 2) and the cylinder for a combustion chamber 12, similar to that of the first embodiment. The combustion chamber main body 11 is connected to the combustion chamber basket 13 (see Fig. 2) and the burner 14, similar to that of the first embodiment. The burner 14 comprises the pilot burner 15 and the main burner (burner) 16.

[0085] As described in the first embodiment, the pilot burner 15 and the main burner 16 are arranged in the combustion chamber basket 13, i.e., the end section upstream of the transition piece 21 in the direction of flow of the combustion gas Cg. The pilot burner 15 is positioned along the central axis of the combustion chamber basket 13. A plurality of the main burners 16 (eight in Fig. 7) is arranged around the pilot burner 15 in the circumferential direction of the combustion chamber basket 13. In the present embodiment, the main burners 16 are arranged at equal intervals in the circumferential direction of the combustion chamber basket 13. The number of main burners 16 can be freely determined.

[0086] The cylinder for a combustion chamber 12 of the present embodiment is provided with the supply opening extension section 30 including the annular channel section 34 and the plurality of cylindrical channel sections 35 similarly to the first embodiment.

[0087] In the present embodiment, the positions of the cylindrical channel sections 35 in the circumferential direction are aligned with the positions in the circumferential direction of the centers of the main burners 16. Furthermore, in the present embodiment, the majority of the cylindrical channel sections 35 are arranged at equal intervals in the circumferential direction of the transition piece 21.

[0088] In the present embodiment, the number of cylindrical channel sections 35 corresponds to the number of main burners 16, as shown in Fig. Figure 7 is shown. However, as long as the majority of cylindrical channel sections 35 are arranged at equal intervals in the circumferential direction of the transition piece 21, the number of cylindrical channel sections 35 can, for example, be greater or less than the number of main burners 16.

[0089] If the number of cylindrical channel sections 35 is less than the number of main burners 16, the number of cylindrical channel sections 35 can be, for example, 1 / 2, 1 / 3, 1 / 4, etc., of the number of main burners 16. If the number of cylindrical channel sections 35 is greater than the number of main burners 16, the number of cylindrical channel sections 35 can be, for example, an integer multiple (2 times, 3 times, 4 times, etc.) of the number of main burners 16. In such a case, some of the multiple cylindrical channel sections 35 have their positions in the circumferential direction aligned with the circumferential positions of the centers of the main burners 16, and the other cylindrical channel sections 35 are offset in the circumferential direction of the transition piece 21 from the circumferential position of the centers of the main burners 16.

[0090] In the transition piece 21 of the present embodiment, as for example in Fig. As shown in Figure 8, a part of the majority of downstream supply openings 25A of the first cooling channels 22, which are arranged in the circumferential direction of the transition piece 21, are aligned at the positions in the circumferential direction of the cylindrical channel sections 35, which are aligned with the positions in the circumferential direction of the centers of the main burners 16.

[0091] According to the cylinder for a combustion chamber 12 and the combustion chamber 2 and gas turbine GT, which is provided with the same, of the present embodiment, and configured as described above, the same effect is achieved as in the first embodiment.

[0092] According to the cylinder for a combustion chamber 12 of the present embodiment, the upstream area 21A of the transition piece 21 (see Fig. 3 and Fig. 4) be cooled more efficiently. In particular, the amount of heat from the main burner 16 is maximized at the wall section of the upstream region 21A of the transition piece 21 at the circumferential sections of the transition piece 21 that correspond to the circumferential positions of the centers of the main burners 16, and minimized at the circumferential sections of the transition piece 21 that is located adjacent to the main burners 16 in the circumferential direction. In the cylinder for a combustion chamber 12 of the present embodiment, the circumferential positions of the cylindrical channel sections 35 are aligned with the circumferential positions of the centers of the main burners 16. Consequently, the first cooling air supplied to the annular channel section 34 from the cylindrical channel sections 35 reaches the sections of the wall of the transition piece 21 that are heated most by the main burners 16 that are closest together.In other words, the sections of the wall of the transition piece 21 that are heated most by the main burners 16 can be cooled efficiently. Accordingly, the wall section of the transition piece 21 can be cooled efficiently using a small amount of initial cooling air.

[0093] In the present embodiment, by arranging the plurality of cylindrical channel sections 35 at equal intervals in the circumferential direction of the transition piece 21, unevenly distributed cooling by the first cooling fluid, which is fed into the annular channel section 34, in the circumferential direction of the transition piece 21 in the upstream region 21A of the transition piece 21 can be prevented. Consequently, the cylinder for a combustion chamber 12 can be cooled more efficiently and uniformly. By improving the uniform cooling of the cylinder for a combustion chamber 12, the amount of first cooling fluid required for cooling the cylinder for a combustion chamber 12 can be reduced.

[0094] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a third embodiment according to the present invention with reference to Fig. 9 described. In the third embodiment, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations thereof are omitted.

[0095] As in Fig. Figure 9 shows the cylinder for a combustion chamber 12 of the present embodiment with the supply opening extension section 30, including the annular channel section 34 and the cylindrical channel section 35, similar to that provided in the first embodiment. The sections of the annular channel section 34 and the cylindrical channel section 35 that are located downstream of the downstream supply opening 25A in the direction of flow of the combustion gas Cg are formed by the first wall section 31. The sections of the annular channel section 34 and the cylindrical channel section 35 that are located upstream of the downstream supply opening 25A in the direction of flow of the combustion gas Cg are formed by the second wall section 32.

[0096] In the present embodiment, the supply opening extension section 30 is provided with a thermal insulation layer 37, which reduces heat conduction at the first wall section 31 and the second wall section 32. In the illustrated example, the thermal insulation layer 37 is provided on the side of the first wall section 31 and the second wall section 32 facing the housing interior 10A. However, the thermal insulation layer 37 could, for example, be provided on the side facing the guide channel 33.The thermal insulation layer 37 is formed, for example, by thermal spraying a thermal spray application material with a low coefficient of thermal conductivity (for example, ceramic-based material with a low coefficient of thermal conductivity) onto the surface of the first wall section 31 and the second wall section 32 (the side facing the housing interior 10A or the guide channel 33).

[0097] Alternatively, the first wall section 31 and the second wall section 32 can be subdivided, for example, in the thickness direction, and an air layer formed in the free space between the first wall section 31 and the second wall section 32 can be the thermal insulation layer 37.

[0098] According to the cylinder for a combustion chamber 12 of the present embodiment, the same effect is achieved as in the first embodiment. According to the cylinder for a combustion chamber 12 of the present embodiment, the thermal insulation layer 37 prevents the heat of the high-temperature air, which is released from the outlet opening 27 of the second cooling channel 23, from being transferred to the first cooling air in the guide channel 33 of the extension section of the supply opening 30 via the first wall section 31 or the second wall section 32. In other words, the heating of the first cooling air supplied to the guide channel 33 can be prevented. Consequently, the upstream area 21A of the transition piece 21 can be efficiently cooled by the first cooling air.

[0099] The configuration of the third embodiment described above can also be applied to the cylinder for a combustion chamber of the second embodiment described above.

[0100] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a fourth embodiment according to the present invention with reference to Fig. 10 described. In the fourth embodiment, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations thereof are omitted.

[0101] As in Fig. As shown in Figure 10, the cylinder for a combustion chamber 12 of the present embodiment is configured similarly to that of the first embodiment. However, in the present embodiment, the supply opening extension section 30 of the cylinder for a combustion chamber 12 is not supported by the outer circumferential surface 21c of the transition piece 21. The supply opening extension section 30 of the present embodiment is supported by the acoustic lining 24. In particular, the supply opening extension section 30 is attached to the acoustic lining 24 by a support section 38. The support section 38 is connected to the supply opening extension section 30 and the acoustic lining 24, for example, by welding, brazing, or the like. In the illustrated example, the support section 38 is connected to the annular channel section 34.But the support section 38 can, for example, be connected to the cylindrical channel section 35.

[0102] The support section 38 can, for example, have a rod-like shape extending from the acoustic lining 24 to the supply opening extension section 30. In this case, a plurality of support sections 38 can be arranged in the circumferential direction of the transition piece 21. The support section 38 can, for example, have a circular arc-like or ring-shaped form extending in the circumferential direction of the transition piece 21.

[0103] According to the cylinder for a combustion chamber 12 and the combustion chamber 2 and gas turbine GT, which is provided with the same, of the present embodiment, and configured as described above, the same effect is achieved as in the first embodiment.

[0104] According to the cylinder for a combustion chamber 12 of the present embodiment, the supply opening extension section 30 is supported by the acoustic lining 24. Consequently, the need to attach the supply opening extension section 30 to the outer circumferential surface 21c of the transition piece 21 is eliminated. Therefore, an increase in thermal stress on the transition piece 21 caused by attaching the supply opening extension section 30 can be prevented to a greater extent than in a case where the supply opening extension section 30 is attached to the transition piece 21 by welding or the like.

[0105] The configuration of the fourth embodiment described above can also be applied to the configuration of the second and third embodiments described above.

[0106] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine is provided according to a fifth embodiment of the present invention with reference to Fig. 11 and Fig. 12 described. In the fifth embodiment, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations thereof are omitted.

[0107] As in Fig. 11 and Fig. As shown in Figure 12, the cylinder for a combustion chamber 12 of the present embodiment, with the supply opening extension section 30 including the first wall section 31 and the second wall section 32, is similar to that provided in the first embodiment. The guide channel 33 is formed between the first wall section 31 and the second wall section 32. The guide channel 33 directs the compressed air Ca, which becomes the first cooling air, from the housing interior 10A to the downstream supply opening 25A of the first cooling channel 22. The opening section 33A of the guide channel 33 to the housing interior 10A is spaced apart from the outer circumferential surface 21c of the transition piece 21.

[0108] However, in the present embodiment, the opening section 33A of the guide channel 33 is located downstream of the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg and points downstream in the flow direction of the combustion gas Cg. Accordingly, the first wall section 31 and the second wall section 32 of the present embodiment extend outwards in the radial direction of the transition piece 21 from the outer circumferential surface 21c of the transition piece 21, then curve or bend to extend downstream from the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg.Consequently, the sections of the second wall section 32, which extend downstream in the direction of flow of the combustion gas Cg, are located further out in the radial direction of the transition piece 21 than the sections of the first wall section 31, which extend downstream in the direction of flow of the combustion gas Cg.

[0109] In the illustrated example, the tip is located in the direction of travel of the first wall section 31, which extends downstream in the direction of flow of the combustion gas Cg, relative to the tip in the direction of travel of the second wall section 32 in the direction of flow of the combustion gas Cg downstream. However, the tip in the direction of travel of the first wall section 31 must be located upstream of the tip in the direction of travel of the second wall section 32 in the direction of flow of the combustion gas Cg.

[0110] In the cylinder for a combustion chamber 12 of the present embodiment, the first wall section 31 and the second wall section 32 form the annular channel section 34 in a similar manner to those in the first embodiment. The first wall section 31 and the second wall section 32 also form the cylindrical channel section 35 in a similar manner to those in the second embodiment.

[0111] In the present embodiment, however, the opening section 33A of the guide channel 33 described above points downstream in the flow direction of the combustion gas Cg. Consequently, the cylindrical channel section 35 extends straight downstream from the annular channel section 34 in the flow direction of the combustion gas Cg from the outlet opening 27 of the second cooling channel 23. In the present embodiment, a plurality of the cylindrical channel sections 35 are arranged at intervals around the circumference of the transition piece 21.

[0112] The circumferential positions of the cylindrical channel sections 35, which are arranged in the circumferential direction of the transition piece 21, can be aligned with the circumferential positions of the downstream supply openings 25A, which are arranged in the circumferential direction of the transition piece 21, as for example in Fig. 12 are shown, arranged. But the positions in the circumferential direction of the cylindrical channel sections 35 can also be offset in the circumferential direction of the transition piece 21 with the position in the circumferential direction of the downstream supply opening 25A.

[0113] According to the cylinder for a combustion chamber 12 and the combustion chamber 2 and gas turbine GT, which is provided with the same, of the present embodiment, and configured as described above, the same effect is achieved as in the first embodiment.

[0114] According to the cylinder for a combustion chamber 12 of the present embodiment, the opening section 33A of the guide channel 33 of the extension section of the supply opening 30, which is spaced apart from the outer circumferential surface 21c of the transition piece 21, is located downstream of the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg and points downstream in the flow direction of the combustion gas Cg. Therefore, it is correspondingly prevented that high-temperature air (second cooling air), which is released from the outlet opening 27 of the second cooling channel 23, which opens towards the outer circumferential surface 21c of the transition piece 21, enters the guide channel 33.

[0115] According to the cylinder for a combustion chamber 12 of the present embodiment, the opening section 33A of the guide channel 33 points downstream in the flow direction of the combustion gas Cg. Consequently, the compressed air Ca, which flows from downstream to upstream in the flow direction of the combustion gas Cg, can be efficiently supplied to the housing interior 10A.

[0116] According to the cylinder for a combustion chamber 12 of the present embodiment, the length of the sections of the first wall section 31 and the second wall section 32, which extend in the radial direction of the transition piece 21 from the outer circumferential surface 21c of the transition piece 21, can be reduced to a shorter length than in cases such as the first embodiment, in which the opening section 33A of the guide channel 33 is directed outwards in the radial direction of the transition piece 21.

[0117] The configuration of the fifth embodiment described above can also be applied to the configuration of the second to fourth embodiments described above.

[0118] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a sixth embodiment according to the present invention with reference to Fig. 13 and Fig. 15 described. In the sixth embodiment, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations thereof are omitted.

[0119] As in Fig. 13, Fig. 14 to Fig. As shown in Figure 15, the cylinder for a combustion chamber 12 of the present embodiment, with the supply opening extension section 30 including the first wall section 31 and the second wall section 32, is similar to that provided in the first embodiment. The guide channel 33 is formed between the first wall section 31 and the second wall section 32. The guide channel 33 directs the compressed air Ca, which becomes the first cooling air, from the housing interior 10A to the downstream supply opening 25A of the first cooling channel 22. The opening section 33A of the guide channel 33 to the housing interior 10A is spaced apart from the outer circumferential surface 21c of the transition piece 21. The opening section 33A of the guide channel 33 is directed outwards in the radial direction of the transition piece 21, and the first wall section 31 and the second wall section 32 extend outwards in the radial direction of the transition piece 21.

[0120] However, in the present embodiment, the first wall section 31 and the second wall section 32 are formed circumferentially around the entire transition piece 21 to form only the annular channel section 34, which is connected to the downstream supply opening 25A. In other words, the cylinder for a combustion chamber 12 of the present embodiment is provided with the annular channel section 34, but not with the cylindrical channel sections 35, as in the first embodiment. Accordingly, the opening section 33A of the guide channel 33 of the present embodiment is formed circumferentially around the entire transition piece 21.

[0121] The supply opening extension section 30, which is located in Fig. 13 and Fig. Figure 14 is provided with a connecting section 36A, which is connected to a first chamber 10A1 and a second chamber 10A2 of the housing interior 10A in a similar manner to that of the first embodiment. The first chamber 10A1 is located downstream of the first wall section 31 in the direction of flow of the combustion gas Cg, and the second chamber 10A2 is located upstream of the second wall section 32 in the direction of flow of the combustion gas Cg.

[0122] The connecting section 36A of the present embodiment is formed by a cylindrical element arranged between the first wall section 31 and the second wall section 32. Both ends of the cylindrical element open to the first chamber 10A1 and the second chamber 10A2, which are described above. In the illustrated example, a plurality of cylindrical elements are arranged at intervals in the circumferential direction of the transition piece 21, but the cylindrical element is not limited to such a configuration.

[0123] As an alternative, the supply opening extension section 30, which is in Fig. 15 is shown, not with the connecting section 36A (see Fig. 13 and Fig. 14) is provided for and can only include the first wall section 31 and the second wall section 32.

[0124] According to the cylinder for a combustion chamber 12 and the combustion chamber 2 and gas turbine GT, which is provided with the same, of the present embodiment, and configured as described above, the same effect is achieved as in the first embodiment.

[0125] According to the cylinder for a combustion chamber 12 of the present embodiment, the first wall section 31 and the second wall section 32 of the extension section of the supply opening 30 form only the annular channel section 34. Consequently, the supply opening extension section 30 can be manufactured by using the first wall section 31 and the second wall section 32 with a simple shape. Therefore, the cylinder for a combustion chamber 12 can be manufactured at low cost.

[0126] The configuration of the sixth embodiment described above can also be applied to the cylinder for a combustion chamber of the third to fifth embodiments described above.

[0127] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a seventh embodiment of the present invention is described with reference to Fig. 16 described. In the seventh embodiment, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations thereof are omitted.

[0128] As in Fig. As shown in Figure 16, the cylinder for a combustion chamber 12 of the present embodiment, with the supply opening extension section 30 including the first wall section 31 and the second wall section 32, is similar to that provided in the first embodiment. The guide channel 33 is formed between the first wall section 31 and the second wall section 32. The guide channel 33 directs the compressed air Ca, which becomes the first cooling air, from the housing interior 10A to the downstream supply opening 25A of the first cooling channel 22. The opening section 33A of the guide channel 33 to the housing interior 10A is spaced apart from the outer circumferential surface 21c of the transition piece 21.

[0129] However, the supply opening extension section 30 of the present embodiment is formed integrally with the transition piece 21. In other words, the first wall section 31 and the second wall section 32 are formed integrally with the transition piece 21 in order to project from the outer circumferential surface of the transition piece 21.

[0130] The opening section 33A of the guide channel 33 can, for example, be formed around the entire transition piece 21 in the circumferential direction in a similar manner to that of the sixth embodiment. Additionally, the first wall section 31 and the second wall section 32 can be formed as a plurality of cylindrical elements subdivided in the circumferential direction of the transition piece 21, similar to the cylindrical channel sections 35 of the first embodiment. If a plurality of opening sections 33A are formed, only one supply opening extension section 30 can be provided for the downstream supply opening 25A of each of the first cooling channels 22.

[0131] According to the cylinder for a combustion chamber 12 of the present embodiment, the same effect is achieved as in the first embodiment. According to the cylinder for a combustion chamber 12 of the present embodiment, by integrally forming the extension section of the supply opening 30 with the transition piece 21, an increase in the thermal stress on the transition piece 21 caused by attaching the extension section of the supply opening 30 can be prevented to a greater extent than in a case where the supply opening extension section 30 is attached to the transition piece 21 by welding or the like.

[0132] The configuration of the seventh embodiment described above can also be applied to the cylinder for a combustion chamber of the second to sixth embodiments described above.

[0133] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine is provided according to an eighth embodiment of the present invention with reference to Fig. 17 and Fig. 20 described. In the eighth embodiment, components that are identical to those of the embodiments described above have the same reference symbols in the drawings, and explanations thereof are omitted.

[0134] As in Fig. 17 and Fig. As shown in Figure 18, in the cylinder for a combustion chamber 12 of the present embodiment, the first wall section 31 and the second wall section 32 are formed circumferentially around the entirety of the transition piece 21 in order to form only the annular channel section 34, which is connected to the downstream supply opening 25A, and in a similar manner to the second example of the fifth embodiment, which is shown in Fig. Figure 15 is shown. Accordingly, the opening section 33A of the guide channel 33 is formed in the circumferential direction around the entirety of the transition piece 21.

[0135] The cylinder for a combustion chamber 12 of the present embodiment is provided with a prevention section 39, which prevents the compressed air Ca from entering the annular channel section 34 from the space outside the transition piece 21. A pair of prevention sections 39 is provided at opposite positions in the radial direction of the transition piece 21.

[0136] In the present embodiment, each prevention section 39 comprises the opening section 33A of the guide channel 33, which is formed by the annular channel section 34. Each prevention section 39 comprises a portion of the opening section 33A in the circumferential direction of the transition piece 21 and not the entire opening section 33A. In other words, the cross-sectional view taken along line BB in the direction of the arrow in Fig. 17, the cross-sectional shape which is in Fig. Figure 15 is shown. The range of angle α, which is the range in which each prevention section 39 extends in the circumferential direction of the transition piece 21, is, for example, preferably 60° to 90°. The pair of prevention sections 39 has the same size.

[0137] According to the cylinder for a combustion chamber 12 of the present embodiment, the compressed air Ca can be supplied to the first cooling channel 22 from the downstream supply opening 25A even if the compressed air Ca flows in a direction that intersects the axis of the transition piece 21, and consequently the upstream area 21A of the transition piece 21 can be cooled more efficiently. The details are described below.

[0138] If, for example, in Fig. As shown in Figure 17, the compressed air Ca, which flows in the direction of flow of the compressed air Ca in the housing interior 10A near the transition piece 21, comprises a component of a flow direction that is perpendicular to the axial direction of the transition piece 21 (the direction from bottom to top in Fig. 17) The compressed air Ca flows along a circumferential direction that corresponds to the circumference of the transition piece 21. When this happens, the flow velocity distribution and static pressure distribution in the circumferential direction near the circumference of the transition piece 21 are as shown in the graphs of Fig. 19 and Fig. 20 is shown.

[0139] In the graphs of Fig. 19 and Fig. 20, from the transition piece 21, the position in the circumferential direction of the downstream flow direction of the compressed air Ca is used as a standard position (0°) and the position in the circumferential direction of the upstream flow direction is determined to be 180°. In the graphs of Fig. 19 and Fig. 20 The intermediate positions in the circumferential direction between the upstream and downstream flow direction (intermediate circumferential position) of the transition piece 21 are determined to be 90° and -90°.

[0140] According to the graphs of Fig. 19 and Fig. 20 The flow velocity of the compressed air Ca near the circumference of the transition piece 21 increases from the upstream flow direction position of the transition piece 21 towards the intermediate circumferential position and decreases from the intermediate circumferential position towards the downstream flow direction position. Consequently, the static pressure of the compressed air Ca near the circumference of the transition piece 21 decreases from the upstream flow direction position of the transition piece 21 towards the intermediate circumferential position and increases from the intermediate circumferential position towards the downstream flow direction position.

[0141] If the prevention section 39 is therefore not provided, the amount of compressed air Ca supplied to the first cooling channel 22 from the downstream supply opening 25A, located at or near the intermediate circumferential position, is reduced due to the low static pressure at and near the intermediate circumferential position of the transition piece 21 in the guide channel 33. Alternatively, as in Fig. As shown in Figure 17, the prevention section 39 is located at a position based on the intermediate circumferential position of the transition piece 21. This allows the drop in static pressure in the guide channel 33 to be suppressed at and near the intermediate circumferential position of the transition piece 21. Accordingly, compressed air Ca can be efficiently supplied to the first cooling channel 22 from the downstream supply opening 25A, which is located at or near the intermediate circumferential position, and consequently, the upstream area 21A of the transition piece 21 can be cooled more efficiently.

[0142] The configuration of the eighth embodiment described above can be applied to a cylinder for a combustion chamber in which the annular channel section 34 is formed by at least the first wall section 31 and the second wall section 32. In other words, the configuration of the eighth embodiment can be applied to the cylinder for a combustion chamber including the annular channel section 34 of the first to seventh embodiments.

[0143] If, for example, in Fig. As shown in Figure 4, where the first wall section 31 and the second wall section 32 form the annular channel section 34 and the cylindrical channel section 35, the prevention section 39 can be provided at the opening section 33A of the guide channel 33, as in the eighth embodiment described above. However, the prevention section 39 can also be provided in the cylindrical channel section 35 or at the boundary between the annular channel section 34 and the cylindrical channel section 35.

[0144] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a ninth embodiment according to the present invention with reference to Fig. 21 described. In the ninth embodiment, components that are identical to those of the embodiments described above have the same reference symbols in the drawings, and explanations thereof are omitted.

[0145] As in Fig. As shown in Figure 21, in the cylinder for a combustion chamber 12 of the present embodiment, the first wall section 31 and the second wall section 32 are formed circumferentially around the entirety of the transition piece 21 in order to form only the annular channel section 34, which is connected to the downstream supply opening 25A, and this in a similar manner to that of the second example of the fifth embodiment, which is shown in Fig. 15, and the eighth embodiment, which is shown in Fig. 17 and Fig. Figure 18 is shown. Accordingly, the opening section 33A of the guide channel 33 is formed circumferentially around the entire transition piece 21. The cross-sectional view, taken along line DD in the direction of the arrow in Fig. 21 corresponds to the cross-sectional shape that is in Fig. 15 is shown.

[0146] The cylinder for a combustion chamber 12 of the present embodiment is provided with a separating section 300, which divides the annular channel section 34 in the circumferential direction of the transition piece 21. In the present embodiment, a pair of separating sections 300 is formed at opposite positions in the radial direction of the transition piece 21.

[0147] In the present embodiment, each separating section 300 is formed by a plurality of separating plates 301, which are arranged at intervals in the circumferential direction of the transition piece 21. In the present embodiment, each of the separating sections 300 consists of two separating plates 301. Accordingly, the annular channel section 34 is divided into an even number (four in the illustrated example) of subdivided, annular channel sections 34A, 34B, 34C, 34D, which are arranged in the circumferential direction of the transition piece 21. The distance between the two separating plates 301 of each separating section 300 in the circumferential direction, i.e., the range of angle β between the two separating plates 301, is, for example, preferably between 60° and 90°.

[0148] According to the cylinder for a combustion chamber 12 of the present embodiment, the compressed air Ca can be supplied to the first cooling channel 22 from the downstream supply opening 25A even if the compressed air Ca flows in a direction that intersects the axis of the transition piece 21, and consequently the upstream area 21A of the transition piece 21 can be cooled more efficiently. The details are described below.

[0149] If, for example, in Fig. Figure 21 shows the flow direction of the compressed air Ca in the housing interior 10A near the transition piece 21, a component of the flow direction perpendicular to the axial direction of the transition piece 21 (the direction from bottom to top in Fig. 21), the compressed air Ca flows inside the housing 10A along a circumferential direction that corresponds to the circumference of the transition piece 21. When this happens, the flow velocity distribution and static pressure distribution in the circumferential direction near the circumference of the transition piece 21 become similar to those shown in the graphs of Fig. 19 and Fig. 20 of the eighth embodiment is shown.

[0150] If the separating section 300 is therefore not provided, the quantity of compressed air Ca supplied to the first cooling channel 22 from the downstream supply opening 25A, which is located at the intermediate circumferential position of the transition piece 21 (at a position that is 90° and -90° in Fig. 21 corresponds) or nearby, reduced.

[0151] If, as an alternative, as in Fig. As shown in Figure 21, the separating sections 300 are provided at positions based on the intermediate circumferential positions of the transition piece 21. The flow of compressed air Ca in the circumferential direction of the transition piece 21 is blocked by the separating sections 300 at the divided, annular channel sections 34A, 34B, 34C, 34D. Consequently, the reduction of static pressure at each divided, annular channel section 34A, 34B, 34C, 34D can be suppressed. In particular, the reduction of static pressure at the divided, annular channel sections 34C, 34D, which are located at the intermediate circumferential positions, can be suppressed. Accordingly, compressed air Ca can be efficiently supplied to the first cooling channel 22 from the downstream supply opening 25A, which is located at or near the intermediate circumferential position of the transition piece 21, and consequently the upstream area 21A of the transition piece 21 can be cooled more efficiently.

[0152] The configuration of the ninth embodiment described above can be applied to a cylinder for a combustion chamber in which the annular channel section 34 is formed by at least the first wall section 31 and the second wall section 32. In other words, the configuration of the ninth embodiment can be applied to the cylinder for a combustion chamber including an annular channel section 34 of the first to eighth embodiments.

[0153] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine according to a tenth embodiment of the present invention is described.

[0154] In the cylinder for a combustion chamber 12 of the present embodiment, the first wall section 31 and the second wall section 32 are formed circumferentially around the entirety of the transition piece 21 to form the annular channel section 34, which is connected to the downstream supply opening 25A, and in a similar manner to those of the first to ninth embodiments, which are described in Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9, Fig. 10, Fig. 11, Fig. 12, Fig. 13, Fig. 14, Fig. 15, Fig. 16, Fig. 17, Fig. 18, Fig. 19, Fig. 20 to Fig. 21. In the present embodiment, the channel cross-section of the annular channel section 34, which is perpendicular to the circumferential direction of the transition piece 21, is equal to or greater than 50 times the opening area of ​​the downstream supply opening 25A of the outer circumferential surface 21c of the transition piece 21.

[0155] If, according to the cylinder for a combustion chamber of the present embodiment, the channel cross-section of the annular channel section 34 is equal to or greater than 50 times the opening area of ​​the downstream supply opening 25A, a pressure loss of the first cooling air (compressed air Ca) supplied to the annular channel section 34 from the housing interior 10A can be suppressed when the first cooling air flows circumferentially around the annular channel section 34. In other words, even when the first cooling air flows circumferentially around the annular channel section 34, the reduction of the static pressure in the annular channel section 34 can be suppressed. Consequently, the first cooling air in the annular channel section 34 can be efficiently supplied to the first cooling channel 22.Since a pressure difference in the annular channel section 34 can be suppressed in the circumferential direction, a difference in the flow rate of the first cooling air supplied to the majority of first cooling channels arranged in the circumferential direction can be suppressed.

[0156] According to the cylinder for a combustion chamber of the present embodiment, the resistance can be kept low when the first cooling air is supplied to the first cooling channel 22 from the annular channel section 34 via the downstream supply opening 25A. Consequently, the first cooling air can be supplied to the first cooling channel 22 smoothly.

[0157] Now, a cylinder for a combustion chamber, a combustion chamber and a gas turbine is described according to a non-inventive example with reference to Fig. 22 and Fig. 23 described. In the example, components that are identical to those of the first embodiment have the same reference symbols in the drawings, and explanations of these are omitted.

[0158] As in Fig. 22 and Fig. As shown in Figure 23, the cylinder for a combustion chamber 12A of the present embodiment is provided with the transition piece 21 (cylindrical element), which is similar to that of the first embodiment, the first cooling channel 22, the second cooling channel 23, and the acoustic lining 24. However, the cylinder for a combustion chamber 12A is not equipped with the supply opening extension section 30 of the first embodiment (see Figure 23). Fig. 4 and Fig. 5) is provided and is instead provided with the guide wall sections 40A, 40B.

[0159] The guide wall sections 40A, 40B are formed between the downstream supply opening 25A of the first cooling channel 22 and the outlet opening 27 of the second cooling channel 23 and extend away from the outer circumferential surface 21c of the transition piece 21. In the present embodiment, the guide wall sections 40A, 40B extend outwards in the radial direction of the transition piece 21. The compressed air Ca (fluid), which flows upstream in the housing interior 10A from downstream in the flow direction of the combustion gas Cg, is guided by the guide wall sections 40A, 40B from the downstream supply opening 25A in the circumferential direction of the transition piece 21 and upstream from the downstream supply opening 25A in the flow direction of the combustion gas Cg. The reference numerals f1, f2 in Fig. 22 and Fig. 23 indicate the directions in which the compressed air Ca is directed from the guide wall sections 40A, 40B into the housing interior 10A.

[0160] The guide wall section 40A, which is in Fig. The transition piece 21, as shown in Figure 22, is inclined, when viewed from the outside in the radial direction of the transition piece 21, in the direction of the flow of the combustion gas Cg upstream of the downstream supply opening 25A towards the circumferential sides of the transition piece 21. The guide wall section 40A, which is in Fig. The guide wall section 40A, as shown in Figure 22, is formed to clamp the downstream supply opening 25A in the radial direction of the transition piece 21 when viewed from the outside. The guide wall section 40A can be in a U-shape (circular arc shape) when viewed from the outside in the radial direction of the transition piece 21, as shown in Figure 22. Fig. It can be represented as 22, but it can also be formed in a V-shape, for example.

[0161] The guide wall section 40B, which is in Fig. The transition piece 23, as shown in Figure 23, is provided with a first plate-like wall section 41, a second plate-like wall section 42, and a third plate-like wall section 43. Viewed from the outside in the radial direction of the transition piece 21, the first plate-like wall section 41 extends circumferentially between the downstream supply opening 25A of the first cooling channel 22 and the outlet opening 27 of the second cooling channel 23; the second plate-like wall section 42 extends upstream from a first end section 41A of the first plate-like wall section 41 in the direction of flow of the combustion gas Cg; and the third plate-like wall section 43 extends downstream from a second end section 41B of the first plate-like wall section 41 in the direction of flow of the combustion gas Cg.

[0162] The first end section 41A and the second end section 41B of the first plate-like wall section 41 are offset on opposite sides in the circumferential direction of the transition piece 21 from the downstream supply opening 25A of the first cooling channel 22 and the outlet opening 27 of the second cooling channel 23. The first end section 41A of the first plate-like wall section 41 is located upstream of the second end section 41B in the direction of flow of the combustion gas Cg. In other words, the plate-like wall section 41 extends in a direction that is inclined in the radial direction of the transition piece 21, relative to the circumferential direction of the transition piece 21 when viewed from the outside.

[0163] The second plate-like wall section 42 is located adjacent to one side in the circumferential direction of the transition piece 21 of the downstream supply opening 25A of the first cooling channel 22. The second plate-like wall section 42 extends upstream of the downstream supply opening 25A in the flow direction of the combustion gas Cg.

[0164] The third plate-like wall section 43 is located adjacent to the other side in the circumferential direction of the transition piece 21 of the outlet opening 27 of the second cooling channel 23. The third plate-like wall section 43 extends downstream of the downstream supply opening 25A in the flow direction of the combustion gas Cg.

[0165] According to the cylinder for a combustion chamber 12A of the present example, which is configured as such, even if compressed air Ca in the housing interior 10A flows in the direction opposite to the flow direction of the combustion gas Cg in the transition piece 21, the guide wall sections 40A, 40B prevent high-temperature air, which is released from the outlet opening 27 of the second cooling channel 23, from entering the first cooling channel 22 from the downstream supply opening 25A.

[0166] The compressed air Ca, which flows in the housing interior 10A in the opposite direction to the flow direction of the combustion gas Cg, is guided by the guide wall sections 40A and 40B in the circumferential direction of the transition piece 21 and in the flow direction of the combustion gas Cg upstream of the downstream supply opening 25A. Consequently, if the high-temperature air flows upstream of the downstream supply opening 25A in the flow direction of the combustion gas Cg due to the flow of the compressed air Ca in the housing interior 10A, the guide wall sections 40A and 40B can prevent the high-temperature air from reaching the downstream supply opening 25A. Accordingly, it can be prevented that the high-temperature air, after flowing upstream from the downstream supply opening 25A in the direction of flow of the combustion gas Cg, enters the first cooling channel 22 from the downstream supply opening 25A.

[0167] According to the cylinder for a combustion chamber 12A and the combustion chamber 2 and gas turbine GT, which is provided with it, as in the example described above, it can be more reliably prevented that the high-temperature air, which is discharged from the outlet opening 27 of the second cooling channel 23, enters the first cooling channel 22, and the upstream area 21A of the transition piece 21 can be cooled more efficiently by the first low-temperature cooling fluid, which is fed into the first cooling channel 22. In other words, the cooling effect of the cylinder for a combustion chamber 12A can be improved.

[0168] For example, in the first to seventh embodiments, the first wall section 31 and the second wall section 32 of the extension section of the supply opening 30 can have a cylindrical shape, and, for example, only the majority of cylindrical channel sections 35, which are connected to the downstream supply openings 25A, are cylindrical in the circumferential direction of the transition piece 21, as shown in Fig. 24 and Fig. 25, arranged at intervals. In other words, the supply opening extension section 30 can be provided with the majority of cylindrical channel sections 35, but not the annular channel section 34. In this case, similarly to the first embodiment, the spaces between the cylindrical channel sections 35 adjacent in the circumferential direction serve as the connecting sections 36.

[0169] In the first to ninth embodiments, the first wall section 31 and the second wall section 32 can, for example, extend in an inclination in the flow direction of the combustion gas Cg downstream from the outer circumferential surface 21c of the transition piece 21 outwards in the radial direction of the transition piece 21.

[0170] In embodiments one through nine, the supply opening extension section 30 need not be located at the supply opening 25 of the first cooling channel 22, but can instead be located at the outlet opening 27 of the second cooling channel 23. In this case, the high-temperature air released from the outlet opening 27 of the second cooling channel 23 is discharged by the supply opening extension section 30 into the housing interior 10A at a position spaced apart from the outer circumferential surface 21c of the transition piece 21. Accordingly, the high-temperature air has difficulty reaching the supply opening 25 of the first cooling channel 22, which opens directly into the housing interior 10A at the outer circumferential surface 21c of the transition piece 21. In other words, the entry of the high-temperature air into the first cooling channel 22 can be prevented.

[0171] In the fifth embodiment, the opening section 33A of the guide channel 33 can point in a direction other than downstream in the flow direction of the combustion gas Cg. In the fifth embodiment, the opening section can be located upstream 33A from the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg, or it can be located in a position aligned with the outlet opening 27 in the flow direction of the combustion gas Cg.

[0172] In particular, if the opening section 33A of the guide channel 33 is located downstream of the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg, the opening section 33A can point in any direction except downstream in the flow direction of the combustion gas Cg.

[0173] If, for example, the opening section 33A of the guide channel 33 is inclined downwards in the flow direction of the combustion gas Cg in a direction in the radial direction of the transition piece 21, or is turned outwards in the radial direction of the transition piece 21, the opening section 33A can be located upstream of the outlet opening 27 of the second cooling channel 23 in the flow direction of the combustion gas Cg, or can be located in a position aligned with the outlet opening 27 in the flow direction of the combustion gas Cg.

[0174] In these cases, in a similar manner to those of the fifth embodiment, it can be prevented that the high-temperature air released from the outlet opening 27 of the second cooling channel 23 enters the guide channel 33.

[0175] The present invention can be applied to a cylinder for a combustion chamber, a combustion chamber and a gas turbine and is designed to improve the cooling effect of a cylinder for a combustion chamber. List of reference symbols GT Gas Turbine 1 compressor 2 Combustion chamber 3 Turbine 10A Housing interior (space outside the transition piece 21) 12, 12A cylinders for one combustion chamber 14 burners 15 pilot burners 16 main burners (burners) 21 Transition piece (cylindrical element) 21A Upstream area 21B Downstream area 21c External perimeter area 22 First cooling channel 23 Second cooling channel 24 Acoustic lining 25 Supply opening 25A Downstream supply opening 27 Outlet opening 30 Supply opening extension section 31 First wall section 32 Second wall section 33 Guide channel 33A Opening section 34 Ring-shaped canal section 34A, 34B, 34C, 34D Subdivided annular channel section 35 Cylindrical canal section 36, 36A Connection section 37 Thermal insulation layer 38 Support section 39 Prevention section 40A, 40B Guide wall section 300 separation section 301 Dividing plate Ca compressed air (fluid) Cg combustion gas

Claims

[1] Cylinder (12) for a combustion chamber through which a combustion gas flows during operation and which is configured to supply the combustion gas (Cg) to a turbine (3), wherein the cylinder (12) for a combustion chamber comprises the following: a cylindrical element (21) extending along an axis, a first cooling channel (22) which is formed in an upstream region (21A) which is located upstream in a flow direction of the combustion gas (Cg) of a wall section of the cylindrical element (12), wherein the first cooling channel (22) comprises a supply opening (25,25A) which opens to an outer circumferential surface (21c) of the cylindrical element (21) and is configured to cool the upstream region (21A) via a first cooling fluid (Ca) which is supplied via the supply opening (25,25A) from a space (10A) outside the cylindrical element (21), a second cooling channel (23) which is formed in a downstream region (21B) located downstream in the direction of flow of the combustion gas (Cg) of the wall section of the cylindrical element (21) next to the upstream region (21A), wherein the second cooling channel (23) is configured to cool the downstream region (21B) by means of supplied second cooling fluid, and has an outlet opening (27) which opens to the outer circumferential surface (21c) of the cylindrical element (21) downstream of the supply opening (25,25A) in the flow direction of the combustion gas (Cg) and is configured to discharge the second cooling fluid into the space (10A) outside the cylindrical element (21), and a supply opening extension section (30) comprising the following: a first wall section (31) which is arranged between the supply opening (25,25A) and the outlet opening (27) extending in a direction away from the outer circumferential surface (21c) of the cylindrical element (21), a second wall section (32) which is arranged upstream of the supply opening (25,25A) in the flow direction of the combustion gas (Cg), wherein the second wall section (32) extends in a direction away from the outer circumferential surface (21c) of the cylindrical element (21), and a guide channel (33) formed between the first wall section (31) and the second wall section (32), wherein the guide channel (33) is configured to direct the first cooling fluid (Ca) from the space (10A) outside the cylindrical element (21) to the supply opening (25,25A). [2] Cylinder (12) for a combustion chamber according to claim 1, wherein the guide channel (33) comprises an opening section (33A) to the space (10A) outside the cylindrical element (21), which is directed outwards in a radial direction of the cylindrical element (21). [3] Cylinder (12) for a combustion chamber according to claim 1, wherein the guide channel (33) has an opening section (33A) to the space (10A) outside the cylindrical element (21) which points downstream in the flow direction of the combustion gas (Cg) and is located downstream of the outlet opening (27) in the flow direction of the combustion gas (Cg). [4] Cylinder (12) for a combustion chamber according to one of claims 1 to 3, wherein the first wall section (31) and the second wall section (32) are formed in a circumferential direction around an entirety of the cylindrical element (21) to form an annular channel section (34) which is connected to the supply opening (25,25A). [5] Cylinder (12) for a combustion chamber according to claim 4, further comprising: a pair of prevention sections (39) configured to prevent the first cooling fluid (Ca) from entering the annular channel section (34) from the space (10A) outside the cylindrical element (21), the pair of prevention sections (39) being arranged at opposite positions in the radial direction of the cylindrical element (21). [6] Cylinder (12) for a combustion chamber according to claim 4 or 5, further comprising: a separation section (300) that divides the annular channel section (34) in the circumferential direction. [7] Cylinder (12) for a combustion chamber according to claim 6, wherein a pair of the separating sections (300) is arranged in opposite positions in the radial direction of the cylindrical element (21). [8] Cylinder (12) for a combustion chamber according to one of claims 4 to 7, wherein a channel cross-section of the annular channel section (34) perpendicular to the circumferential direction of the cylindrical element (21) is equal to or greater than 50 times an opening area of ​​the supply opening (25,25A). [9] Cylinder (12) for a combustion chamber according to one of claims 4 to 8, wherein the first wall section (31) and the second wall section (32) are formed in a cylindrical shape to form a cylindrical channel section (35) which is connected to the annular channel section (34) and the space (10A) outside the cylindrical element (21). [10] Cylinder (12) for a combustion chamber according to claim 9, wherein a plurality of the cylindrical channel sections (35) are arranged at intervals in the circumferential direction of the cylindrical element (21). [11] Cylinder (12) for a combustion chamber according to one of claims 1 to 3, wherein a plurality of the supply openings (25, 25A) are arranged at intervals in a circumferential direction of the cylindrical element (21), and a plurality of the first wall sections (31) and the second wall sections (32) are formed in cylindrical shapes to form a plurality of cylindrical channel sections (35) which are arranged at intervals in the circumferential direction of the cylindrical element (21), wherein each of the plurality of cylindrical channel sections (35) is connected to one of the plurality of supply openings (25, 25A). [12] Cylinder (12) for a combustion chamber according to claim 10 or 11, wherein positions in the circumferential direction of the plurality of cylindrical channel sections (35) are aligned to positions in the circumferential direction of centers of a plurality of burners (16) which are provided at an end section of the cylindrical element which is located upstream in the flow direction of the combustion gas (Cg) and are arranged in the circumferential direction of the cylindrical element (21). [13] Cylinder (12) for a combustion chamber according to claim 12, wherein the plurality of cylindrical channel sections (35) are arranged at equal intervals in the circumferential direction of the cylindrical element (21). [14] Cylinder (12) for a combustion chamber according to one of claims 1 to 13, wherein the supply opening extension section (30) comprises a connecting section (36, 36A) which is connected to a first space (10A1) of the space (10A) outside the cylindrical element (21) which is located downstream of the first wall section (31) in the direction of flow of the combustion gas (Cg) and to a second space (10A2) of the space (10A) outside the cylindrical element (21) which is located upstream of the second wall section (32) in the direction of flow of the combustion gas (Cg). [15] Cylinder (12) for a combustion chamber according to any one of claims 1 to 14, wherein the supply opening extension section (30) has a thermal insulation layer (37) configured to reduce heat conduction at the first wall section (31) and at the second wall section (32). [16] Cylinder (12) for a combustion chamber according to one of claims 1 to 15, wherein the supply opening extension section (30) is supported by the outer circumferential surface (21c) of the cylindrical element (21). [17] Cylinder (12) for a combustion chamber according to any one of claims 1 to 15, further comprising: an acoustic lining (24) which is provided upstream of the supply opening extension section (30) of the cylindrical element (21) in the flow direction of the combustion gas (Cg), wherein the supply opening extension section (30) is supported by the acoustic lining (24). [18] Cylinder (12) for a combustion chamber according to one of claims 1 to 15, wherein the supply opening extension section (30) is formed integrally with the cylindrical element (21). [19] Combustion chamber (2), comprising: a cylinder (12) for a combustion chamber according to one of claims 1 to 18, and a burner (16) configured to inject fuel. [20] Gas turbine (GT), comprising: a combustion chamber (2) according to claim 19, a compressor (1) configured to generate compressed air to be supplied to the combustion chamber (2), and a turbine (3) with a rotor (4) configured to be rotated by combustion gas (Cg) supplied from the combustion chamber (2).

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