Patent ID: 12247499

DESCRIPTION OF EMBODIMENTS

Hereinafter, various embodiments of gas turbine equipment according to the present invention and modification examples thereof will be described in detail with reference to the drawings.

First Embodiment

Hereinafter, a first embodiment of the gas turbine equipment according to the present invention will be described with reference toFIGS.1to5.

As illustrated inFIG.1, the gas turbine equipment of the present embodiment includes a gas turbine10and a cooling device70that cools some components of the gas turbine10.

The gas turbine10includes a compressor20that compresses air A; a plurality of combustors40that combust fuel in the air, which has been compressed by the compressor20, to generate combustion gas G; and a turbine30that is driven by the combustion gas G.

The compressor20includes a compressor rotor21that rotates around a rotor axis Lr; a compressor casing25that rotatably covers the compressor rotor21; an d a plurality of stator vane rows26. Hereinafter, a direction in which the rotor axis Lr extends is referred to as a rotor axial direction Da, and one side and the other side in the rotor axial direction Da are referred to as an axial upstream side Dau and an axial downstream side Dad, respectively. In addition, a circumferential direction around the rotor axis Lr is simply referred to as a circumferential direction Dc, and a direction perpendicular to the rotor axis Lr is referred as a radial direction Dr. Further, a side approaching the rotor axis Lr in the radial direction Dr is referred to as a radial inner side Dri, and an opposite side is referred to as a radial outer side Dro.

The compressor rotor21includes a rotor shaft22extending along the rotor axis Lr in the rotor axial direction Da, and a plurality of rotor blade rows23attached to the rotor shaft22. The plurality of rotor blade rows23are arranged in the rotor axial direction Da. Each of the rotor blade rows23is formed of a plurality of rotor blades arranged in the circumferential direction Dc. One stator vane row26of the plurality of stator vane rows26is disposed on the axial downstream side Dad of each of the plurality of rotor blade rows23. Each of the stator vane rows26is provided inside the compressor casing25. Each of the stator vane rows26is formed of a plurality of stator vanes arranged in the circumferential direction Dc. An annular space between the radial outer side Dro of the rotor shaft22and the radial inner side Dri of the compressor casing25in a region in which the stator vanes and the rotor blades are disposed in the rotor axial direction Da forms an air compression flow path in which the air is compressed while flowing therethrough.

The turbine30is disposed on the axial downstream side Dad of the compressor20. The turbine30includes a turbine rotor31that rotates around the rotor axis Lr; a turbine casing35that rotatably covers the turbine rotor31; and a plurality of stator vane rows36. The turbine rotor31includes a rotor shaft32extending along the rotor axis Lr in the rotor axial direction Da, and a plurality of rotor blade rows33attached to the rotor shaft32. The plurality of rotor blade rows33are arranged in the rotor axial direction Da. Each of the rotor blade rows33is formed of a plurality of rotor blades arranged in the circumferential direction Dc. One stator vane row36of the plurality of stator vane rows36is disposed on the axial upstream side Dau of each of the plurality of rotor blade rows33. Each of the stator vane rows36is provided inside the turbine casing35. Each of the stator vane rows36is formed of a plurality of stator vanes arranged in the circumferential direction Dc. An annular space between the radial outer side Dro of the rotor shaft32and the radial inner side Dri of the turbine casing35in a region in which the stator vanes and the rotor blades are disposed in the rotor axial direction Da forms a combustion gas flow path through which the combustion gas G from the combustors40flows.

The compressor rotor21and the turbine rotor31are located on the same rotor axis Lr, and are connected to each other to form a gas turbine rotor11. For example, a rotor of a generator GEN is connected to the gas turbine rotor11. The gas turbine10further includes an intermediate casing16having a tubular shape and having the rotor axis Lr as a center. The intermediate casing16is disposed between the compressor casing25and the turbine casing35in the rotor axial direction Da. The compressor casing25and the turbine casing35are connected to each other via the intermediate casing16. The compressor casing25, the intermediate casing16, and the turbine casing35are connected to each other to form a gas turbine casing15. Compressed air Acom from the compressor20flows into the intermediate casing16. The plurality of combustors40are provided in the intermediate casing16.

The cooling device70includes a cooling air line71, a cooler75, and a boost compressor76. The cooling air line71bleeds the compressed air Acom in the intermediate casing16from the inside of the intermediate casing16, and guides the compressed air Acom to the combustors40. The cooling air line71includes an air bleeding line72, a cooling air main line73, and a plurality of cooling air branch lines74. The air bleeding line72is connected to the intermediate casing16, and guides the compressed air Acom in the intermediate casing16to the boost compressor76. The cooling air main line73is connected to a discharge port of the boost compressor76. Enhanced cooling air Acl that is air boosted by the boost compressor76flows through the cooling air main line73. The cooling air branch line74is a line branching from the cooling air main line73to each of the plurality of combustors40. Each of the plurality of cooling air branch lines74guides the enhanced cooling air Acl to one of the combustors40. The cooler75and the boost compressor76are provided in the air bleeding line72of the cooling air line71. The cooler75cools the compressed air Acom flowing through the air bleeding line72. The boost compressor76boosts the compressed air Acom that has been cooled by the cooler75, and feeds the compressed air Acom to the combustors40as the enhanced cooling air Acl.

As illustrated inFIG.2, the combustor40includes a transition piece (or combustion pipe)50that feeds the high-temperature and high-pressure combustion gas G into the combustion gas flow path of the turbine30, and a fuel nozzle41that injects fuel F into the transition piece50, together with the compressed air Acom. The fuel nozzle41includes a plurality of burners42that inject the fuel F into the transition piece50, and a frame43that supports the plurality of burners42. A fuel line45is connected to each of the burners42. The fuel line45is provided with a fuel flow rate-regulating valve46that regulates the flow rate of the fuel F to be supplied to the plurality of burners42. The transition piece50of the combustor40is disposed inside the intermediate casing16.

The transition piece50includes a pipe51having a tubular shape around a combustor axis Lcom; an acoustic damper61forming an acoustic space Ss on an outer peripheral side of the pipe51; a cooling air jacket65forming a cooling air space Sa on the outer peripheral side of the pipe51; and an attachment flange66. Hereinafter, a direction in which the combustor axis Lcom extends is referred to as a combustor axial direction Dcom (hereinafter, simply referred to as an axial direction Dcom). In addition, one side in the axial direction Dcom is referred to as a combustor upstream side Dcu (hereinafter, simply referred to as an upstream side Dcu), and the other side in the axial direction Dcom is referred to as a combustor downstream side Dcd (hereinafter, simply referred to as a downstream side Dcd).

The pipe51includes an inlet opening54iformed at an end on the upstream side Dcu; an outlet opening54oformed at an end on the downstream side Dcd; an outer peripheral surface55ofacing the outer peripheral side; and an inner peripheral surface55ifacing an inner peripheral side. A space on the inner peripheral side of the pipe51is a combustion space Sc in which the fuel F is combusted and through which the combustion gas G generated by the combustion flows. The attachment flange66extends from the outer peripheral surface55oof the pipe51to the outer peripheral side at an end on the downstream side Dcd of the pipe51. The attachment flange66is a flange for attaching the pipe51to the turbine casing35.

The acoustic damper61includes a part of a panel forming the pipe51, and an acoustic cover62forming the acoustic space Ss on the outer peripheral side of the pipe51in conjunction with the part of the pipe51. The acoustic cover62is provided in a portion on the upstream side Dcu of the pipe51. The acoustic cover62extends in the circumferential direction with respect to the combustor axis Lcom.

The cooling air jacket65forms the cooling air space Sa on the outer peripheral side of the pipe51in conjunction with another part except for the portion forming the acoustic damper61in the panel forming the pipe51, and the attachment flange66. For this reason, a part of an edge of the cooling air jacket65is in contact with the attachment flange66, and the remainder of the edge of the cooling air jacket65is in contact with the pipe51. The cooling air space Sa is isolated from an outer space So that is a space on the outer peripheral side of the pipe51. The outer space So is a space on the outer peripheral side of the pipe51and inside the intermediate casing16, excluding the acoustic space Ss and the cooling air space Sa. During operation of the gas turbine10, the compressed air Acom that has been discharged from the compressor20is present in the outer space So. In addition, the fact that the cooling air space Sa is isolated from the outer space So means that the compressed air Acom in the outer space So does not directly flow into the cooling air space Sa. As described above, the cooling air jacket65is in contact with the attachment flange66provided at the end on the downstream side Dcd of the pipe51, which means that the cooling air jacket65is located on the downstream side Dcd of the acoustic cover62. The cooling air branch lines74of the cooling device70described above are connected to the cooling air jacket65. Therefore, the enhanced cooling air Acl from the cooling device70flows into the cooling air space Sa.

As illustrated inFIGS.3and4, the pipe51includes a plurality of acoustic holes59, a plurality of first air flow paths56, and a plurality of third air flow paths58.FIG.3is a sectional view of a main part of the transition piece50taken along a virtual plane including the combustor axis Lcom, andFIG.4is a view on arrow IV inFIG.3.

The acoustic hole59penetrates through the panel forming the pipe51from the acoustic space Ss to the combustion space Sc. Therefore, the acoustic hole59is a hole penetrating through a portion of the pipe51, which is covered by the acoustic cover62, from the outer peripheral surface55oto the inner peripheral surface55iof the pipe51.

Both the first air flow path56and the third air flow path58are formed between the outer peripheral surface55oand the inner peripheral surface55iof the pipe51. The first air flow path56includes an inlet56ithat faces the cooling air space Sa and that guides the air in the cooling air space Sa into the first air flow path56, and an outlet56othat faces the acoustic space Ss and that guides the air, which has passed through the first air flow path56, into the acoustic space Ss. Therefore, the inlet56iof the first air flow path56is formed in a portion of the outer peripheral surface55oof the pipe51, the portion being covered by the cooling air jacket65. In addition, the outlet56oof the first air flow path56is formed in a portion of the outer peripheral surface55oof the pipe51, the portion being covered by the acoustic cover62. The third air flow path58includes an inlet58ithat faces the cooling air space Sa and that guides the air in the cooling air space Sa into the third air flow path58, and an outlet58othat faces the outer space So and that guides the air, which has passed through the third air flow path58, into the outer space So. Therefore, the inlet58iof the third air flow path58is formed in a portion of the outer peripheral surface55oof the pipe51, the portion being covered by the cooling air jacket65. In addition, the outlet58oof the third air flow path58is formed in a portion of the outer peripheral surface55oof the pipe51, the portion not being covered by the acoustic cover62and the cooling air jacket65. Among the plurality of third air flow paths58, the outlets58oof some of the third air flow paths58are formed in a portion on the upstream side Dcu of the outer peripheral surface55oof the pipe51with respect to the portion covered by the acoustic cover62.

As illustrated inFIG.5, the panel forming the pipe51is formed by joining an outer peripheral wall panel52oand an inner peripheral wall panel52iby means of brazing or the like. A plurality of grooves53that are recessed in a direction away from the other side and that are long in the axial direction Dcom are formed in one wall panel of the outer peripheral wall panel52oand the inner peripheral wall panel52i. An air flow path56(58) through which the air flows is formed between an inner surface of the groove53and a surface of the other wall panel. In the present embodiment, the grooves53are formed in the outer peripheral wall panel52o.

Next, an operation of the gas turbine10described above will be described.

The compressor20suctions outside air A, and compresses the air while the air passes through the air compression flow path. The compressed air, namely, the compressed air Acom, flows from the air compression flow path of the compressor20into the intermediate casing16. The compressed air Acom is supplied into the pipe51of the transition piece50via the fuel nozzle41of the combustor40. The fuel F is injected into the pipe51of the transition piece50from the plurality of burners42of the fuel nozzle41. The fuel F is combusted in the compressed air Acom that has been supplied into the combustion space Sc of the pipe51. As a result of the combustion, the combustion gas G is generated, and the combustion gas G flows from the transition piece50into the combustion gas flow path of the turbine30. When the combustion gas G passes through the combustion gas flow path, the turbine rotor31rotates.

While the fuel F is combusted in the combustion space Sc, the boost compressor76of the cooling device70is driven. For this reason, the compressed air Acom in the outer space So, in other words, some of the compressed air Acom in the intermediate casing16, is bled from the inside of the intermediate casing16, flows into the cooler75of the cooling device70, and then is cooled here. The compressed air Acom that has been cooled in the cooler75is boosted by the boost compressor76, and then flows into the cooling air space Sa of the transition piece50as the enhanced cooling air Acl. Since the enhanced cooling air Acl is air obtained by cooling and then boosting the compressed air Acom in the intermediate casing16, the enhanced cooling air Acl has a lower temperature and a higher pressure than those of the compressed air Acom in the intermediate casing16.

The enhanced cooling air Acl in the cooling air space Sa flows into the first air flow path56and the third air flow path58of the pipe51to flow through the air flow paths56and58. The enhanced cooling air Acl is heated while cooling the pipe51because of heat exchange with the pipe51, which is exposed to the high-temperature combustion gas G, in the process of flowing through the air flow paths56and58.

The enhanced cooling air Acl that has passed through the third air flow path58flows out to the outer space So from the outlet58oof the third air flow path58, and is mixed with the compressed air Acom present in the outer space So. In addition, the enhanced cooling air Acl that has passed through the first air flow path56flows from the outlet56oof the first air flow path56into the acoustic space Ss. The enhanced cooling air Acl that has flowed into the acoustic space Ss flows out to the combustion space Sc from the acoustic hole59. For this reason, the combustion gas G in the combustion space Sc does not flow into the acoustic space Ss.

In order to ensure that the combustion gas G in the combustion space Sc does not flow into the acoustic space Ss, a pressure Ps in the acoustic space Ss needs to be higher than a pressure Pc in the combustion space Sc, and a pressure difference ΔP between both pressures (=Ps−Pc>0) needs to be a certain value or more.

The pressure difference ΔP is proportional to a density p of a fluid and is proportional to the square of a flow velocity v of the fluid as expressed by the following equation.
Δ∝ρ·v2

As can be understood from the above equation, when the pressure difference ΔP is to be set to the certain value or more, increasing the flow velocity v of the fluid is more effective than increasing the density p of the fluid. In addition, the flow velocity v of a fluid is increased by increasing the volume of the fluid while reducing the density p of the fluid, so that the mass flow rate of the fluid flowing out from the acoustic space Ss to the combustion space Sc can be suppressed. As a method for increasing the volume of the fluid while reducing the density p of the fluid, there is a method in which the fluid is expanded by increasing the amount of heating of the fluid.

Here, in order to facilitate understanding of the following description, a comparative example of this aspect will be described. A pipe of the comparative example does not include the first air flow path56, but includes a second air flow path57illustrated by an imaginary line (alternate long and two short dashed line) inFIG.3. The second air flow path57is formed between the outer peripheral surface55oand the inner peripheral surface55iof the pipe51. The second air flow path57includes an inlet57ithat faces the outer space So and that guides the air in the outer space So into the second air flow path57, and an outlet57othat faces the acoustic space Ss and that guides the air, which has passed through the second air flow path57, into the acoustic space Ss. The inlet57iof the second air flow path57is located on the upstream side Dcu of the acoustic cover62. The air in the outer space So flows into the second air flow path57from the inlet57iof the second air flow path57to flow through the second air flow path57. The air is heated while cooling the pipe because of heat exchange with the pipe51, which is exposed to the combustion gas G, in the process of flowing through the second air flow path57. The air that has passed through the second air flow path57flows from the outlet57oof the second air flow path57into the acoustic space Ss. The air that has flowed into the acoustic space Ss flows out to the combustion space Sc from the acoustic hole59.

In the comparative example, when the air in the outer space So, namely, the compressed air Acom, has a constant pressure and a constant temperature, as a method for increasing the amount of heating of the air flowing through the second air flow path57, for example, there is a method for lengthening the flow path length of the second air flow path57. In this method, the following problems occur.

(1) There is a possibility that the pressure loss in the second air flow path57increases, so that the air in the outer space So does not reach the acoustic space Ss, or does not flow out to the combustion space Sc from the acoustic hole59.

(2) There is a possibility that the temperature of the air becomes very high by the time the air reaches the acoustic space Ss, so that the air has no capability to cool the pipe51.

In addition, there is also another method for forming the second air flow path57in a region of the pipe51which is easily heated by the combustion gas G. Even in this method, the above problem (2) occurs.

In the present embodiment, the enhanced cooling air Acl in the cooling air space Sa isolated from the outer space So flows through the first air flow path56. Therefore, in the present embodiment, the air having a pressure and a temperature different from those of the compressed air Acom in the outer space So is capable of flowing through the first air flow path56. Therefore, in the present embodiment, the enhanced cooling air Acl having a higher pressure and a lower temperature than those of the compressed air Acom in the outer space So flows through the first air flow path56. For this reason, in the present embodiment, as the method for increasing the amount of heating of the air, even when the method for lengthening the flow path length of the first air flow path56and/or the method for forming the first air flow path56in a region of the pipe51which is easily heated by the combustion gas G are adopted, the above problems (1) and (2) do not occur.

Therefore, in the present embodiment, the pressure difference ΔP (=Ps−Pc) between the pressure Ps in the acoustic space Ss and the pressure Pc in the combustion space Sc is set to the certain value or more, so that while the air is allowed to flow out from the acoustic space Ss to the combustion space Sc on the inner peripheral side of the pipe51, the mass flow rate of the air can be suppressed.

As described above, in the present embodiment, since the mass flow rate of the air flowing out from the acoustic space Ss to the combustion space Sc on the inner peripheral side of the pipe51can be suppressed, the amount of NOx generated can be suppressed. Further, in the present embodiment, since the amount of the combustion gas G diluted by the air flowing out to the combustion space Sc is decreased, a reduction in the temperature of the gas to be fed to the turbine30can be suppressed, and a reduction in the efficiency of the gas turbine10can be suppressed.

In the present embodiment, as the method for increasing the amount of heating of the air, the method for lengthening the flow path length of the first air flow path56and the method for forming the first air flow path56in a region of the pipe51which is easily heated by the combustion gas G are adopted. Specifically, in the present embodiment, the flow path length of the first air flow path56is lengthened by providing the cooling air jacket65in a portion on the downstream side Dcd of the pipe51, and allowing the cooling air space Sa in the cooling air jacket65and the acoustic space Ss in the acoustic damper61, which is disposed in a portion on the upstream side Dcu of the pipe51, to communicate with each other through the first air flow path56. In the combustion space Sc of the pipe51, the temperature on the downstream side Dcd from a tip portion of a flame formed by the combustion of the fuel F is higher than the temperature on the upstream side Dcu from the tip portion of the flame. Therefore, a region on the downstream side Dcd of the pipe51is more easily heated by the combustion gas G than a region on the upstream side Dcu. Therefore, in the present embodiment, the first air flow path56is formed in a region on the downstream side Dcd of the pipe51which is easily heated.

In the present embodiment, as described above, as the method for increasing the amount of heating of the air, the method for lengthening the flow path length of the first air flow path56and the method for forming the first air flow path56in a region of the pipe51which is easily heated by the combustion gas G are both adopted. However, only one of the above two methods may be adopted.

Second Embodiment

Hereinafter, a second embodiment of the gas turbine equipment according to the present invention will be described with reference toFIGS.6and7. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the first embodiment only in the configuration of the transition piece of the combustor. Therefore, hereinafter, a configuration of a transition piece50aof the present embodiment will be mainly described.

Similarly to the first embodiment, the transition piece50aof the present embodiment includes a pipe51a; the acoustic damper61; the cooling air jacket65; and the attachment flange66. Similarly to the pipe51of the first embodiment, the pipe51aincludes the inlet opening54i; the outlet opening54o; the outer peripheral surface55o; the inner peripheral surface55i; a plurality of the first air flow paths56; and a plurality of the third air flow paths58. The pipe51aof the present embodiment further includes a plurality of the second air flow paths57. The second air flow path57is formed between the outer peripheral surface55oand the inner peripheral surface55iof the pipe51a. The second air flow path57includes the inlet57ithat faces the outer space So and that guides the compressed air Acom in the outer space So into the second air flow path57, and the outlet57othat faces the acoustic space Ss and that guides the compressed air Acom, which has passed through the second air flow path57, into the acoustic space Ss. The inlet57iof the second air flow path57is located on the upstream side Dcu of the acoustic cover62. The pipe51aof the present embodiment includes the third air flow path58, but may not include the third air flow path58.

Also in the present embodiment, similarly to the first embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first air flow path56and the third air flow path58of the pipe51ato flow through the air flow paths56and58. The enhanced cooling air Acl is heated while cooling the pipe51abecause of heat exchange with the pipe51a, which is exposed to the high-temperature combustion gas G, in the process of flowing through the air flow paths56and58. The enhanced cooling air Acl that has passed through the third air flow path58flows out to the outer space So from the outlet58oof the third air flow path58, and is mixed with the compressed air Acom present in the outer space So. In addition, the enhanced cooling air Acl that has passed through the first air flow path56flows from the outlet56oof the first air flow path56into the acoustic space Ss.

The compressed air Acom in the outer space So flows into the second air flow path57from the inlet57iof the second air flow path57to flow through the second air flow path57. The compressed air Acom is heated while cooling the pipe51abecause of heat exchange with the pipe51a, which is exposed to the combustion gas G, in the process of flowing through the second air flow path57. The compressed air Acom that has passed through the second air flow path57flows from the outlet57oof the second air flow path57into the acoustic space Ss.

Therefore, in the present embodiment, the enhanced cooling air Acl that has flowed through the first air flow path56and the compressed air Acom that has flowed through the second air flow path57flow into the acoustic space Ss. The air that has flowed into the acoustic space Ss flows out to the combustion space Sc through the acoustic hole59. As described above, in the present embodiment, similarly to the first embodiment, since the air flowing out from the acoustic space Ss to the combustion space Sc through the acoustic hole59includes the enhanced cooling air Acl that has flowed through the first air flow path56, the air having a large amount of heating of the air is capable of flowing out to the combustion space Sc. Therefore, also in the present embodiment, similarly to the first embodiment, while the air is allowed to flow out from the acoustic space Ss to the combustion space Sc, the mass flow rate of the air can be suppressed.

In the first embodiment, a portion on the upstream side Dcu of the pipe51with respect to the acoustic cover62is cooled by the air flowing through the third air flow path58. The amount of heating of the air flowing through the third air flow path58by the time the air reaches the acoustic cover62is large. On the other hand, in the present embodiment, the portion on the upstream side Dcu of the pipe51awith respect to the acoustic cover62is cooled by the air flowing through the second air flow path57. In the portion on the upstream side Dcu of the pipe51awith respect to the acoustic cover62, the temperature of the air flowing through the second air flow path57is lower than the temperature of the air flowing through the third air flow path58. For this reason, in the present embodiment, the cooling capacity of the portion on the upstream side Dcu of the pipe51awith respect to the acoustic cover62can be increased more than in the first embodiment.

Third Embodiment

Hereinafter, a third embodiment of the gas turbine equipment according to the present invention will be described with reference toFIGS.8and9. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the first embodiment only in the configuration of the transition piece of the combustor. Therefore, hereinafter, a configuration of a transition piece50bof the present embodiment will be mainly described.

Similarly to the first embodiment, the transition piece50bof the present embodiment includes a pipe51b; acoustic dampers61aand61b; the cooling air jacket65; and the attachment flange66. However, the transition piece50bof the present embodiment includes a plurality of the acoustic dampers61aand61b. Similarly to the pipe51of the first embodiment, the pipe51bincludes the inlet opening54i; the outlet opening54o; the outer peripheral surface55o; the inner peripheral surface55i; a plurality of the first air flow paths56; and a plurality of the third air flow paths58. The outlet56oof the first air flow path56of the present embodiment faces only a first acoustic space Ssa of the first acoustic damper61aof the plurality of acoustic dampers61aand61b, and does not face a second acoustic space Ssb of the second acoustic damper61b. Therefore, in the present embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first acoustic space Ssa through the first air flow path56, but does not flow into the second acoustic space Ssb. The pipe51bof the present embodiment further includes a plurality of the second air flow paths57. The second air flow path57is formed between the outer peripheral surface55oand the inner peripheral surface55iof the pipe51b. The second air flow path57includes the inlet57ithat faces the outer space So and that guides the air in the outer space So into the second air flow path57, and the outlet57othat faces only the second acoustic space Ssb and that guides the air, which has passed through the second air flow path57, into the second acoustic space Ssb. Therefore, in the present embodiment, the compressed air Acorn in the outer space So flows into the second acoustic space Ssb through the second air flow path57, but does not flow into the first acoustic space Ssa. The inlet57iof the second air flow path57is located on the upstream side Dcu of the respective acoustic covers62of the plurality of acoustic dampers61aand61b. The pipe51bof the present embodiment includes the third air flow path58, but may not include the third air flow path58.

Also in the present embodiment, similarly to the first embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first air flow path56and the third air flow path58of the pipe51bto flow through the air flow paths56and58. The enhanced cooling air Acl is heated while cooling the pipe51bbecause of heat exchange with the pipe51b, which is exposed to the high-temperature combustion gas G, in the process of flowing through the air flow paths56and58. The air that has passed through the third air flow path58flows out to the outer space So from the outlet58oof the third air flow path58, and is mixed with the compressed air Acom present in the outer space So. In addition, the enhanced cooling air Acl that has passed through the first air flow path56flows from the outlet56oof the first air flow path56into the first acoustic space Ssa. The air that has flowed into the first acoustic space Ssa flows out to the combustion space Sc from a first acoustic hole59aof the first acoustic damper61a.

The compressed air Acom in the outer space So flows into the second air flow path57from the inlet57iof the second air flow path57to flow through the second air flow path57. The compressed air Acom is heated while cooling the pipe51bbecause of heat exchange with the pipe51b, which is exposed to the combustion gas G, in the process of flowing through the second air flow path57. The compressed air Acom that has passed through the second air flow path57flows from the outlet57oof the second air flow path57into the second acoustic space Ssb. The compressed air Acom that has flowed into the second acoustic space Ssb flows out to the combustion space Sc from a second acoustic hole59bof the second acoustic damper61b.

As described above, in the present embodiment, the enhanced cooling air Acl that has flowed through the first air flow path56flows into the first acoustic space Ssa of a plurality of the acoustic spaces Ss. The air that has flowed into the first acoustic space Ssa flows out to the combustion space Sc through the first acoustic hole59a. For this reason, in the present embodiment, the total mass flow rate of the air flowing out from all the acoustic spaces Ssa and Ssb to the combustion space Sc can be suppressed more than when only the compressed air Acom that has flowed through the second air flow path57flows into all the acoustic spaces Ssa and Ssb.

In addition, in the present embodiment, similarly to the second embodiment, since the second air flow path57is provided, the cooling capacity of the portion on the upstream side Dcu of the pipe51bwith respect to the acoustic cover62can be increased more than in the first embodiment.

Fourth Embodiment

Hereinafter, a fourth embodiment of the gas turbine equipment according to the present invention will be described with reference toFIGS.10and11. The gas turbine equipment of the present embodiment is a modification example of the third embodiment, and differs from the gas turbine equipment of the third embodiment only in the configuration of the transition piece of the combustor. Therefore, hereinafter, a configuration of a transition piece50cof the present embodiment will be mainly described.

Similarly to the third embodiment, the transition piece50cof the present embodiment includes a pipe51c; a plurality of the acoustic dampers61aand61b; the cooling air jacket65; and the attachment flange66. Similarly to the pipe51bof the third embodiment, the pipe51cincludes the inlet opening54i; the outlet opening54o; the outer peripheral surface55o; the inner peripheral surface55i; a plurality of the first air flow paths56; and a plurality of the second air flow paths57. In the present embodiment, among the plurality of first air flow paths56, the outlets56oof some of the first air flow paths56face only the first acoustic space Ssa of the first acoustic damper61aof the plurality of acoustic dampers61aand61b, and do not face the second acoustic space Ssb of the second acoustic damper61b. In addition, among the plurality of first air flow paths56, the outlets56oof the other first air flow paths56face only the second acoustic space Ssb of the second acoustic damper61bof the plurality of acoustic dampers61aand61b, and do not face the first acoustic space Ssa of the first acoustic damper61a. Therefore, in the present embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into each of the acoustic spaces Ssa and Ssb of the plurality of acoustic dampers61aand61bthrough one of the plurality of first air flow paths56. In the present embodiment, among the plurality of second air flow paths57, the outlets57oof some of the second air flow paths57face only the first acoustic space Ssa of the first acoustic damper61aof the plurality of acoustic dampers61aand61b, and do not face the second acoustic space Ssb of the second acoustic damper61b. In addition, among the plurality of second air flow paths57, the outlets57oof the other second air flow paths57face only the second acoustic space Ssb of the second acoustic damper61bof the plurality of acoustic dampers61aand61b, and do not face the first acoustic space Ssa of the first acoustic damper61a. Therefore, in the present embodiment, the compressed air Acom in the outer space So flows into each of the acoustic spaces Ssa and Ssb of the plurality of acoustic dampers61aand61bthrough one of the plurality of second air flow paths57.

As described above, in the present embodiment, similarly to the second embodiment, the enhanced cooling air Acl that has flowed through the first air flow path56and the compressed air Acom that has flowed through the second air flow path57flow into the acoustic spaces Ssa and Ssb of the plurality of acoustic dampers61aand61b, respectively. The air that has flowed into the first acoustic space Ssa flows out to the combustion space Sc through the first acoustic hole59a. The air that has flowed into the second acoustic space Ssb flows out to the combustion space Sc through the second acoustic hole59b. Therefore, also in the present embodiment, similarly to the second embodiment, while the air is allowed to flow out from the acoustic spaces Ssa and Ssb to the combustion space Sc on the inner peripheral side of the pipe51c, the mass flow rate of the air can be suppressed.

The pipe51cof the present embodiment does not include the third air flow path58in each of the above embodiments. However, the pipe51cof the present embodiment may include the third air flow path58.

Fifth Embodiment

Hereinafter, a fifth embodiment of the gas turbine equipment according to the present invention will be described with reference toFIGS.12and13. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the second embodiment only in the configuration of the transition piece of the combustor. Therefore, hereinafter, a configuration of a transition piece50dof the present embodiment will be mainly described.

Similarly to the second embodiment, the transition piece50dof the present embodiment includes the pipe51a; the acoustic damper61; the cooling air jacket65; and the attachment flange66. Similarly to the pipe51aof the second embodiment, the pipe51aincludes the inlet opening54i; the outlet opening54o; the outer peripheral surface55o; the inner peripheral surface55i; a plurality of the first air flow paths56; and a plurality of the third air flow paths58. The pipe51aof the present embodiment further includes a plurality of the second air flow paths57. The pipe51aof the present embodiment includes the third air flow path58, but may not include the third air flow path58.

Also in the present embodiment, similarly to the second embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first air flow path56and the third air flow path58of the pipe51a, and flows through the air flow paths56and58. The enhanced cooling air Acl is heated while cooling the pipe51abecause of heat exchange with the pipe51a, which is exposed to the high-temperature combustion gas G, in the process of flowing through the air flow paths56and58. The enhanced cooling air Acl that has passed through the third air flow path58flows out to the outer space So from the outlet58oof the third air flow path58, and is mixed with the compressed air Acom present in the outer space So. In addition, the enhanced cooling air Acl that has passed through the first air flow path56flows from an outlet156oof the first air flow path56into the acoustic space Ss.

The compressed air Acom in the outer space So flows into the second air flow path57from the inlet57iof the second air flow path57to flow through the second air flow path57. The compressed air Acom is heated while cooling the pipe51abecause of heat exchange with the pipe51a, which is exposed to the combustion gas G, in the process of flowing through the second air flow path57. The compressed air Acom that has passed through the second air flow path57flows from the outlet57oof the second air flow path57into the acoustic space Ss.

Therefore, in the present embodiment, the enhanced cooling air Acl that has flowed through the first air flow path56and the compressed air Acom that has flowed through the second air flow path57flows into the acoustic space Ss from the outlet156oand the outlet57o, respectively. The air that has flowed into the acoustic space Ss flows out to the combustion space Sc through the acoustic hole59. As described above, in the present embodiment, similarly to the first embodiment, since the air flowing out from the acoustic space Ss to the combustion space Sc through the acoustic hole59includes the enhanced cooling air Acl that has flowed through the first air flow path56, the air having a large amount of heating of the air is capable of flowing out to the combustion space Sc. Therefore, also in the present embodiment, similarly to the second embodiment, while the air is allowed to flow out from the acoustic space Ss to the combustion space Sc, the mass flow rate of the air can be suppressed.

In the second embodiment described above, the case has been depicted in which the opening area of the outlet56oand the opening area of the outlet57oare the same; however, in the present embodiment, the opening area of the outlet156othat guides the enhanced cooling air Acl, which has passed through the first air flow path56, into the acoustic space Ss is larger than the opening area of the outlet57othat guides the compressed air Acom, which has passed through the second air flow path57, into the acoustic space Ss. For this reason, in the present embodiment, the flow velocity of the enhanced cooling air Acl flowing from the outlet156ointo the acoustic space Ss can be made lower than the flow velocity of the enhanced cooling air Acl flowing from the outlet56ointo the acoustic space Ss in the second embodiment. Accordingly, since a reduction in static pressure in the acoustic space Ss due to the inflow of the enhanced cooling air Acl can be suppressed, the combustion gas G in the combustion space Sc can be more suppressed from flowing into the acoustic space Ss through the acoustic hole59than in the second embodiment. In addition, in the present embodiment, since the opening area of the outlet156oof the first air flow path56allowing a larger mass flow rate than the second air flow path57is large, a reduction in static pressure in the acoustic space Ss can be efficiently suppressed.

Modification Example of Fifth Embodiment

In the fifth embodiment described above, the case has been depicted in which the outlet156ohaving a larger opening area than that of the outlet57ois formed in the pipe51. In other words, in the fifth embodiment, the case has been described in which one outlet156ois provided in one first air flow path56. However, as illustrated inFIG.14, a plurality of (for example, two) outlets256ofacing the acoustic space Ss may be provided in one first air flow path56. The total opening area of the plurality of outlets256oprovided in one first air flow path56is larger than the opening area of one outlet57o. Also in such a modification example of the fifth embodiment, similarly to the fifth embodiment, the combustion gas G can be suppressed from flowing into the acoustic space Ss by reducing the flow velocity of the enhanced cooling air Acl flowing into the acoustic space Ss.

In addition, instead of the outlet56oof the third and fourth embodiments, the outlet156oof the fifth embodiment or the outlets256oof the modification example of the fifth embodiment may be provided.

INDUSTRIAL APPLICABILITY

According to one aspect of the present invention, while the air is allowed to flow out from the acoustic space of the acoustic damper to the space on the inner peripheral side of the pipe, the mass flow rate of the air can be suppressed.

REFERENCE SIGNS LIST

10: Gas turbine11: Gas turbine rotor15: Gas turbine casing16: Intermediate casing20: Compressor21: Compressor rotor22: Rotor shaft23: Rotor blade row25: Compressor casing26: Stator vane row30: Turbine31: Turbine rotor32: Rotor shaft33: Rotor blade row35: Turbine casing36: Stator vane row40: Combustor41: Fuel nozzle42: Burner43: Frame45: Fuel line46: Fuel flow rate-regulating valve50,50a,50b,50c,50d: Transition piece (or combustion pipe)51,51a,51b,51c: Pipe52i: Inner peripheral wall panel52o: Outer peripheral wall panel53: Groove54i: Inlet opening54o: Outlet opening55i: Inner peripheral surface55o: Outer peripheral surface56: First air flow path56i: Inlet56o,156o,256o: Outlet57: Second air flow path57i: Inlet57o: Outlet58: Third air flow path58i: Inlet58o: Outlet59: Acoustic hole59a: First acoustic hole59b: Second acoustic hole61: Acoustic damper61a: First acoustic damper61b: Second acoustic damper62: Acoustic cover65: Cooling air jacket66: Attachment flange70: Cooling device71: Cooling air line72: Air bleeding line73: Cooling air main line74: Cooling air branch line75: Cooler76: Boost compressorA: AirAcom: Compressed airAcl: Enhanced cooling airG: Combustion gasLcom: Combustor axis (or simply axis)Lr: Rotor axisDa: Rotor axial directionDau: Axial upstream sideDad: Axial downstream sideDc: Circumferential directionDr: Radial directionDri: Radial inner sideDro: Radial outer sideDcom: Combustor axial direction (or simply axial direction)Dcu: Combustor upstream side (or simply upstream side)Dcd: Combustor downstream side (or simply downstream side)Sc: Combustion spaceSs: Acoustic spaceSsa: First acoustic spaceSsb: Second acoustic spaceSa: Cooling air spaceSo: Outer space