TRANSITIONAL PIECE, COMBUSTION CHAMBER, GAS TURBINE AND GAS TURBINE EQUIPMENT

Abstract

Transition piece (50) comprising: a tube (51) having a tubular shape around an axis in which fuel is burned on an inner circumferential side of the tube (51); an acoustic damper (61) comprising part of a plate forming the tube (51) and an acoustic cover (62) which together with the part of the plate forms an acoustic space (Ss) on an outer circumferential side of the tube (51); and a cooling air jacket (65) which, together with another part of the plate forming the tube (51), except for a section forming the acoustic damper (61), forms a cooling air space (Sa), wherein the cooling air space (Sa) is insulated from an external space (So) which is a space on the outer circumferential side of the tube (51), wherein the tube (51) includes an inlet opening (54i) formed at one end on an upstream side which is a side in an axial direction in which the axis extends, and an outlet opening (54o).which is formed at one end on a downstream side, which is the other side in the axial direction, an outer circumferential surface (55o) facing the outer circumferential surface, an inner circumferential surface (55i) facing the inner circumferential surface, a first airflow path (56) formed between the outer circumferential surface (55o) and the inner circumferential surface (55i), a second airflow path (57) formed between the outer circumferential surface (55o) and the inner circumferential surface (55i), and an acoustic hole (59) that penetrates the tube (51) from the acoustic space (Ss) to a combustion chamber, which is a space on the inner circumferential side of the tube (51), and the first airflow path (56) an inlet (56i) facing the cooling air space (Sa) and directing air in the cooling air space (Sa) into the first airflow path (56), and a Outlet (56o), which faces the acoustic space (Ss) and the air that has passed through the first airflow path (56),into the acoustic space (Ss), and the second airflow path (57) contains an inlet (57i) facing the outside space (So) and directs air in the outside space (So) into the second airflow path (57), and an outlet (57o) facing the acoustic space (Ss) and directs the air that has passed through the second airflow path (57) into the acoustic space (Ss).

Description

Technical field

[0001] The present invention relates to a transition piece containing a pipe in which fuel is burned on an inner circumferential side, a combustion chamber containing the transition piece, a gas turbine and gas turbine equipment.

[0002] Priority is claimed by the Japanese patent application No. 2019-097550 filed on May 24, 2019, the contents of which are incorporated herein by reference. State of the art

[0003] A gas turbine comprises a compressor that compresses air to produce compressed air; a combustion chamber that burns fuel in the compressed air; a turbine driven by combustion gases produced by the combustion of the fuel; and an intermediate casing. The compressor includes a compressor rotor and a compressor housing that covers the compressor rotor. The combustion chamber includes a transition piece (or combustion tube) in which fuel is burned on an inner circumferential side, and a burner that injects the fuel into the transition piece. The turbine includes a turbine rotor and a turbine housing that covers the turbine rotor. The compressor housing and the turbine housing are connected to each other via the intermediate casing. The compressed air discharged from the compressor flows into the intermediate casing. The combustion chamber is located within the intermediate casing.

[0004] The following PTL 1 discloses a transition piece for a combustion chamber. The transition piece includes a tube in which fuel is burned on an inner circumferential side; an acoustic damper forming an acoustic space on an outer circumferential side of the tube; and a cooling air jacket forming a cooling air space on the outer circumferential side of the tube. The acoustic damper is located in an upstream section of the tube. The cooling air jacket is located in a downstream section of the tube. Most of the compressed air in the transition piece flows into the combustion chamber. In addition, some of the compressed air in the transition piece is vented from the transition piece. The vented compressed air is amplified by a booster compressor and then flows as amplified cooling air into the cooling air space.A cooling air flow path A and a cooling air flow path B are formed between an outer circumferential surface and an inner circumferential surface of the pipe. An acoustic hole, penetrating the pipe from the outer circumferential surface to the inner circumferential surface, is formed in a section of a plate forming the pipe, with the acoustic damper being formed in this section.

[0005] The cooling air flow path A includes an inlet open in a section of the pipe's outer circumferential surface, forming the cooling air jacket, and an outlet open in a section of the pipe's outer circumferential surface, excluding the acoustic damper and cooling air jacket. The enhanced cooling air in the cooling air space flows into the cooling air flow path A. This enhanced cooling air exchanges heat with the pipe exposed to the combustion gas, thus cooling the pipe as it passes through the cooling air flow path A. After exchanging heat with the pipe, the enhanced cooling air exits the cooling air flow path A outlet into the intermediate housing.

[0006] The cooling air flow path B includes an inlet open in a section of the outer circumferential surface of the pipe, where the acoustic damper and cooling air jacket are not located, and an outlet open in a section of the outer circumferential surface of the pipe, where the acoustic damper is located. Compressed air present in the intermediate housing, which is a space on the outer circumferential side of the pipe, flows into the cooling air flow path B. The compressed air exchanges heat with the pipe exposed to the combustion gas, thus cooling the pipe as it passes through the cooling air flow path B. After the compressed air has flowed into the acoustic space, it exits from the acoustic opening into a space on the inner circumferential side of the pipe.The compressed air flows from the acoustic space through the acoustic hole to the space on the inner circumferential side of the tube in such a way that the high-temperature combustion gas generated in the space on the inner circumferential side of the tube does not flow through the acoustic hole into the acoustic space. List of citations from patent literature

[0007] [PTL 1] Japanese unexamined patent application publication no. 2012-077660 Summary of the invention: Technical problem

[0008] From the perspective of suppressing the amount of NOx produced, it is preferred that the mass flow rate of the air flowing from the acoustic chamber to the chamber on the inner circumferential side of the pipe be small. Since the air flowing from the acoustic chamber to the chamber on the inner circumferential side of the pipe lowers the temperature of the combustion gas produced in the chamber on the inner circumferential side of the pipe, thus reducing the efficiency of the gas turbine, it is further preferred that the mass flow rate of the air be small.

[0009] Therefore, it is an object of the present invention to provide a technique by which, while allowing air to flow from an acoustic space to a space on an inner circumferential side of a tube, the mass flow rate of the air can be suppressed. Solution to the problem

[0010] According to one aspect of the invention for achieving the above objective, an adapter is provided comprising: a tube having a tubular shape about an axis in which fuel is burned on an inner circumferential side of the tube; an acoustic damper comprising a portion of a plate forming the tube and an acoustic cover which, together with the portion of the plate, forms an acoustic space on an outer circumferential side of the tube; and a cooling air jacket which, together with another portion of the plate forming the tube, except for a section forming the acoustic damper, forms a cooling air space, wherein the cooling air space is insulated from an outer space which is a space on the outer circumferential side of the tube.The pipe contains an inlet opening formed at one end on an upstream side, which is one side in an axial direction in which the axis extends; an outlet opening formed at one end on a downstream side, which is the other side in the axial direction; an outer circumferential surface facing the outer circumferential side; an inner circumferential surface facing the inner circumferential side; a first airflow path formed between the outer circumferential surface and the inner circumferential surface; and an acoustic hole that penetrates the pipe from the acoustic space to a combustion chamber, which is a space on the inner circumferential side of the pipe.The first airflow path contains an inlet facing the cooling air space, which directs air in the cooling air space into the first airflow path, and an outlet facing the acoustic space, which directs the air that has passed through the first airflow path into the acoustic space.

[0011] In this scenario, air in the cooling air chamber flows into the first airflow path and continues to flow through it. As it passes through this path, the air is heated by heat exchange with the pipe exposed to combustion gas, while simultaneously cooling the pipe. The air that has traversed the first airflow path then flows from its outlet into the acoustic chamber. The air flowing into the acoustic chamber exits the combustion chamber through the acoustic hole. Therefore, the combustion gas in the combustion chamber does not flow into the acoustic chamber.

[0012] To ensure that the combustion gas in the combustion chamber does not flow into the acoustic space, a pressure Ps in the acoustic space must be higher than a pressure Pc in the combustion chamber, and a pressure difference ΔP between the two pressures (= Ps - Pc > 0) must be a certain value or more.

[0013] The pressure difference ΔP is proportional to the density ρ of a fluid and is proportional to the square of the flow velocity v of the fluid, as expressed by the following equation. ΔP∝ρ⋅v2

[0014] As can be seen from the equation above, increasing the fluid's flow velocity v is more effective than increasing its density ρ when the pressure difference ΔP is to be set to a certain value or higher. Furthermore, increasing the fluid's flow velocity v while simultaneously decreasing its density ρ reduces the mass flow rate of the fluid flowing from the acoustic chamber to the combustion chamber. One method for increasing the fluid's volume and simultaneously decreasing its density ρ involves expanding the fluid by increasing its heating factor.

[0015] To facilitate understanding of the following description, a comparative example of this aspect is presented here. In this example, the pipe does not contain the first airflow path of this aspect, but rather a second airflow path. This second airflow path is formed between the outer and inner circumferential surfaces of the pipe. The second airflow path includes an inlet facing the outside, which directs the air from the outside into the second airflow path, and an outlet facing the acoustic space, which discharges the air that has passed through the second airflow path into the acoustic space. The air in the outside flows from the inlet of the second airflow path into the second airflow path, in order to flow through it.As the air flows through the second airflow path, it is heated by heat exchange with the pipe exposed to the combustion gas, while simultaneously cooling the pipe. The air that has passed through the second airflow path flows from its outlet into the acoustic chamber. From the acoustic hole, the air flowing into the acoustic chamber exits the combustion chamber.

[0016] In the comparative example, if the air in the outside space has a constant pressure and temperature, one method for increasing the amount of heat transferred to the air flowing through the second airflow path is, for example, a method for lengthening the length of the second airflow path. This method presents the following problems. (1) There is a possibility that the pressure loss in the second airflow path increases, so that the air in the outside space does not reach the acoustic space or does not flow out from the acoustic hole to the combustion chamber. (2) There is a possibility that the temperature of the air will become very high by the time the air reaches the acoustic space, so that the air will not be able to cool the pipe.

[0017] Furthermore, there is another method for forming the second airflow path in a region of the pipe that is slightly heated by the combustion gas. Even with this method, the problem described above (2) occurs.

[0018] In this aspect, the air in the cooling air space, which is insulated from the outside, flows through the first airflow path. Therefore, in this aspect, the air, with a pressure and temperature different from those of the air in the outside, is able to flow through the first airflow path. For this reason, since the air supplied to the cooling air space has a higher pressure and a lower temperature than that of the air in the outside, the above problems (1) and (2) do not occur in this aspect, even when the method for increasing the amount of air heated is used, including the method for lengthening the flow path of the first airflow path and / or the method for forming the first airflow path in a region of the pipe that is easily heated by the combustion gas.

[0019] Therefore, in this aspect, the pressure difference ΔP (= Ps - Pc) between the pressure Ps in the acoustic space and the pressure Pc in the combustion chamber Sc is set to a certain value or more, so that, while allowing air to flow from the acoustic space to the combustion chamber on the inner circumferential side of the pipe, the mass flow rate of the air can be suppressed.

[0020] In this aspect, the cooling air jacket of the transition piece can be arranged on the downstream side of the acoustic cover.

[0021] In the combustion chamber, the temperature on the downstream side of the peak of a flame formed by fuel combustion is higher than the temperature on the upstream side of the peak. Therefore, a region on the downstream side of the pipe is heated more readily by the combustion gases than a region on the upstream side. For this reason, the primary airflow path is formed in the more readily heated region on the downstream side of the pipe, thus increasing the amount of heat transferred to the air flowing through this path.

[0022] The transition piece according to this aspect, in which the cooling air jacket is located on the downstream side of the acoustic cover, may include a mounting flange extending from the outer circumferential surface of the pipe to the outer circumferential surface at the end on the downstream side of the pipe. In this case, the cooling air jacket is in contact with the mounting flange.

[0023] Furthermore, in the transition piece, according to one of the aspects above, the pipe can contain a second airflow path formed between the outer and inner circumferential surfaces. In this case, the second airflow path includes an inlet facing the outside, which draws air from the outside into the second airflow path, and an outlet facing the acoustic space, which discharges the air that has passed through the second airflow path into the acoustic space.

[0024] In this respect, a section of the pipe that cannot be cooled by the air flowing through the first airflow path can be cooled by the air flowing through the second airflow path.

[0025] Furthermore, the transition piece can contain several acoustic covers according to one of the aspects mentioned above. In this case, the outlet of the first airflow path faces the acoustic space formed by at least one of the acoustic covers.

[0026] In the transition piece according to this aspect, which contains the multiple acoustic covers, the pipe may include a second airflow path formed between the outer and inner circumferential surfaces. In this case, the second airflow path includes an inlet facing the outside, which directs air from the outside into the second airflow path, and an outlet facing the acoustic space formed by at least one of the multiple acoustic covers, which directs the air that has passed through the second airflow path into the acoustic space.

[0027] In this respect, a section of the pipe that cannot be cooled by the air flowing through the first airflow path can be cooled by the air flowing through the second airflow path.

[0028] In the transition piece according to this aspect, which contains the multiple acoustic covers and the second airflow path, the pipe can contain the first airflow path and the second airflow path for each of the multiple acoustic covers, which communicate with the acoustic space formed by each of the acoustic covers.

[0029] In the transition piece according to one of the above aspects, which contains the second airflow path, the inlet of the second airflow path can be located on the upstream side of the acoustic cover.

[0030] In this respect, a section on the upstream side of the pipe can be cooled with respect to the acoustic covering by the air flowing through the second airflow path.

[0031] In the transition piece according to one of the above aspects, the pipe can contain a third airflow path formed between the outer and inner circumferential surfaces. In this case, the third airflow path includes an inlet facing the cooling air space, which directs the air in the cooling air space into the third airflow path, and an outlet facing the outside, which discharges the air that has passed through the third airflow path into the outside.

[0032] In this respect, a section of the pipe that cannot be cooled by the air flowing through the first airflow path can be cooled by the air flowing through the third airflow path.

[0033] In the transition piece according to this aspect, which contains the second airflow path, the opening area of ​​the outlet that directs the air that has passed through the first airflow path into the acoustic space is larger than the opening area of ​​the outlet that directs the air that has passed through the second airflow path into the acoustic space.

[0034] In this aspect, when the air that has passed through the first airflow path flows into the acoustic space, the flow velocity of the air can be reduced, so that a reduction of static pressure in the acoustic space can be suppressed and the combustion gas can be prevented from flowing into the acoustic space.

[0035] According to one aspect of the invention for achieving the above objective, a combustion chamber is provided comprising: the transition piece according to one of the above aspects; and a burner that injects fuel and air into the combustion chamber.

[0036] According to one aspect of the invention for achieving the above objective, a gas turbine is provided comprising: a combustion chamber; a compressor; a turbine; and an intermediate housing. The compressor includes a compressor rotor rotating about a rotor axis and a compressor housing that covers the compressor rotor. The turbine includes a turbine rotor rotating integrally with the compressor rotor about the rotor axis and a turbine housing that covers the turbine rotor. The intermediate housing is arranged in a rotor axial direction between the compressor housing and the turbine housing, in which the rotor axis extends, and connects the compressor housing and the turbine housing. Compressed air discharged from the compressor flows into the intermediate housing. The combustion chamber is provided in the intermediate housing.

[0037] According to one aspect of the invention for achieving the above objective, gas turbine equipment is provided comprising: the gas turbine according to this aspect; a cooling air duct that directs the compressed air in the intermediate casing to an outside of the intermediate casing and then directs the compressed air into the cooling air jacket; a cooler provided at the cooling air duct that cools the compressed air passing through the cooling air duct; and a booster compressor provided at the cooling air duct that boosts the compressed air that has been cooled by the cooler. Advantageous effects of the invention

[0038] According to one aspect of the present invention, while allowing air to flow from the acoustic space of the acoustic damper to the space on the inner circumferential side of the tube, the mass flow rate of the air can be suppressed. List of characters Fig. Figure 1 is a conceptual view representing a configuration of gas turbine equipment according to a first embodiment of the present invention. Fig. Figure 2 is a sectional view of a main part of the gas turbine equipment according to the first embodiment of the present invention. Fig. Figure 3 is a sectional view of a main part of a transition piece according to the first embodiment of the present invention. Fig. 4 is a view of arrow IV in Fig. 3. Fig. 5 is a section view along line VV in Fig. 3. Fig. Figure 6 is a sectional view of a main part of a transition piece according to a second embodiment of the present invention. Fig. 7 is a view of arrow VII in Fig. 6. Fig. Figure 8 is a sectional view of a main part of a transition piece according to a third embodiment of the present invention. Fig. 9 is a view of arrow IX in Fig. 8. Fig. Figure 10 is a sectional view of a main part of a transition piece according to a fourth embodiment of the present invention. Fig. 11 is a view of arrow XI in Fig. 10. Fig. 12 is a sectional view which Fig. 6 corresponds to a fifth embodiment of the present invention. Fig. 13 is a view that Fig. 7 corresponds to an arrow according to the fifth embodiment of the present invention. Fig. 14 is a view that Fig. 13 corresponds to an arrow in a modification example of the fifth embodiment according to the present invention. Description of embodiments

[0039] Below, various embodiments of gas turbine equipment according to the present invention and examples of modifications thereof are described in detail with reference to the drawings. [First embodiment]

[0040] A first embodiment of the gas turbine equipment according to the present invention is described below with reference to Fig. 1 to Fig. 5 described.

[0041] As in Fig. As shown in Figure 1, the gas turbine equipment of the present embodiment includes a gas turbine 10 and a cooling device 70, which cools some components of the gas turbine 10.

[0042] The gas turbine 10 contains a compressor 20 that compresses air A; several combustion chambers 40 that burn fuel in the air compressed by the compressor 20 to produce combustion gas G; and a turbine 30 that is driven by the combustion gas G.

[0043] The compressor 20 comprises a compressor rotor 21 rotating about a rotor axis Lr; a compressor housing 25 rotatably covering the compressor rotor 21; and several stator blade rows 26. Hereinafter, a direction in which the rotor axis Lr extends is referred to as a rotor axial direction Da, and a side and the other side in the rotor axial direction Da are accordingly referred to as an axial upstream side Dau and an axial downstream side Dad. Furthermore, a circumferential direction about the rotor axis Lr is simply referred to as a circumferential direction Dc, and a direction perpendicular to the rotor axis Lr is referred to as a radial direction Dr. Additionally, a side approaching the rotor axis Lr in the radial direction Dr is referred to as a radial inside Dri, and an opposite side as a radial outside Dro.

[0044] The compressor rotor 21 includes a rotor shaft 22 extending along the rotor axis Lr in the rotor axial direction Da, and several rotor blade rows 23 attached to the rotor shaft 22. The multiple rotor blade rows 23 are arranged in the rotor axial direction Da. Each rotor blade row 23 is formed from multiple rotor blades arranged in the circumferential direction Dc. A stator blade row 26 of the multiple stator blade rows 26 is arranged on the axial downstream side Dad of each of the multiple rotor blade rows 23. Each of the stator blade rows 26 is provided within the compressor housing 25. Each of the stator blade rows 26 is formed from multiple stator blades arranged in the circumferential direction Dc.An annular space between the radial outer surface Dro of the rotor shaft 22 and the radial inner surface Dri of the compressor housing 25 in a region where the stator blades and the rotor blades are arranged in the rotor axial direction Da, forms an air compression flow path in which the air is compressed as it flows through it.

[0045] The turbine 30 is arranged on the axial downstream side Dad of the compressor 20. The turbine 30 comprises a turbine rotor 31 rotating about the rotor axis Lr; a turbine housing 35 rotatably covering the turbine rotor 31; and several stator blade rows 36. The turbine rotor 31 comprises a rotor shaft 32 extending along the rotor axis Lr in the rotor axial direction Da, and several rotor blade rows 33 attached to the rotor shaft 32. The several rotor blade rows 33 are arranged in the rotor axial direction Da. Each of the rotor blade rows 33 is formed from several rotor blades arranged in the circumferential direction Dc. One stator blade row 36 of the several stator blade rows 36 is arranged on the axial upstream side Dau of each of the several rotor blade rows 33. Each of the stator blade rows 36 is provided within the turbine housing 35.Each of the stator blade rows 36 is formed from several stator blades arranged in the circumferential direction Dc. An annular space between the radial outer side Dro of the rotor shaft 32 and the radial inner side Dri of the turbine housing 35 in a region where the stator blades and the rotor blades are arranged in the rotor axial direction Da, forms a combustion gas flow path through which the combustion gas G flows from the combustion chambers 40.

[0046] The compressor rotor 21 and the turbine rotor 31 are arranged on the same rotor axis Lr and are connected to form a gas turbine rotor 11. For example, a generator rotor GEN is connected to the gas turbine rotor 11. The gas turbine 10 further includes an intermediate housing 16 with a tubular shape and the rotor axis Lr as its center. The intermediate housing 16 is arranged in the rotor axial direction Da between the compressor housing 25 and the turbine housing 35. The compressor housing 25 and the turbine housing 35 are connected to each other via the intermediate housing 16. The compressor housing 25, the intermediate housing 16, and the turbine housing 35 are connected to each other to form a gas turbine housing 15. Compressed air Acom from the compressor 20 flows into the intermediate housing 16. The multiple combustion chambers 40 are provided in the intermediate housing 16.

[0047] The cooling device 70 comprises a cooling air duct 71, a radiator 75, and a booster compressor 76. The cooling air duct 71 vents the compressed air Acom from inside the intermediate housing 16 and delivers the compressed air Acom to the combustion chambers 40. The cooling air duct 71 includes a vent duct 72, a main cooling air duct 73, and several cooling air branch ducts 74. The vent duct 72 is connected to the intermediate housing 16 and delivers the compressed air Acom within the intermediate housing 16 to the booster compressor 76. The main cooling air duct 73 is connected to a discharge port of the booster compressor 76. Reinforced cooling air Acl, which is air reinforced by the reinforcing compressor 76, flows through the main cooling air line 73. The cooling air branch line 74 is a line that branches off from the main cooling air line 73 to each of the multiple combustion chambers 40.Each of the multiple cooling air branch lines 74 carries the enhanced cooling air Acl to one of the combustion chambers 40. The cooler 75 and the booster compressor 76 are located in the vent line 72 of the cooling air line 71. The cooler 75 cools the compressed air Acom flowing through the vent line 72. The booster compressor 76 enhances the compressed air Acom, which has been cooled by the cooler 75, and supplies the compressed air Acom to the combustion chambers 40 as the enhanced cooling air Acl.

[0048] As in Fig. As shown in Figure 2, the combustion chamber 40 includes a transition piece (or combustion tube) 50, which supplies the combustion gas G at high temperature and high pressure to the combustion gas flow path of the turbine 30, and a fuel nozzle 41, which injects fuel F together with the compressed air Acom into the exhaust pipe 50. The fuel nozzle 41 includes several burners 42, which inject the fuel F into the transition piece 50, and a frame 43, which supports the multiple burners 42. A fuel line 45 is connected to each of the burners 42. The fuel line 45 is equipped with a fuel flow rate control valve 46, which regulates the flow rate of the fuel F supplied to the multiple burners 42. The transition piece 50 of the combustion chamber 40 is arranged within the intermediate housing 16.

[0049] The transition piece 50 comprises a tube 51 with a tubular shape around a combustion chamber axis Lcom; an acoustic damper 61 forming an acoustic space Ss on an outer circumferential side of the tube 51; a cooling air jacket 65 forming a cooling air space Sa on the outer circumferential side of the tube 51; and a mounting flange 66. Hereinafter, one direction in which the combustion chamber axis Lcom extends is referred to as a combustion chamber axial direction Dcom (hereinafter simply referred to as an axial direction Dcom). Furthermore, one side in the axial direction Dcom is referred to as a combustion chamber 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 combustion chamber downstream side Dcd (hereinafter simply referred to as a downstream side Dcd).

[0050] The tube 51 includes an inlet opening 54i formed at one end on the upstream side Dcu; an outlet opening 54o formed at one end on the downstream side Dcd; an outer circumferential surface 55o facing the outer circumferential side; and an inner circumferential surface 55i facing an inner circumferential side. A space on the inner circumferential side of the tube 51 is a combustion chamber Sc in which the fuel F is burned and through which the combustion gas G generated by the combustion flows. The mounting flange 66 extends from the outer circumferential surface 55o of the tube 51 to the outer circumferential side at one end on the downstream side Dcd of the tube 51. The mounting flange 66 is a flange for attaching the tube 51 to the turbine casing 35.

[0051] The acoustic damper 61 comprises a portion of a plate forming the tube 51 and an acoustic cover 62, which together with the portion of the tube 51 forms the acoustic chamber Ss on the outer circumferential side of the tube 51. The acoustic cover 62 is provided in a section on the upstream side Dcu of the tube 51. The acoustic cover 62 extends circumferentially with respect to the combustion chamber axis Lcom.

[0052] The cooling air jacket 65, together with another part (except for the section forming the acoustic damper 61 in the plate forming the tube 51) and the mounting flange 66, forms the cooling air space Sa on the outer circumferential side of the tube 51. Therefore, part of an edge of the cooling air jacket 65 is in contact with the mounting flange 66, and the remainder of the edge of the cooling air jacket 65 is in contact with the tube 51. The cooling air space Sa is isolated from an external space So, which is a space on the outer circumferential side of the tube 51. The external space So is a space on the outer circumferential side of the tube 51 and within the intermediate casing 16, excluding the acoustic space Ss and the cooling air space Sa. During operation of the gas turbine 10, the compressed air Acom, which was delivered by the compressor 20, is present in the external space So.Furthermore, the fact that the cooling air chamber Sa is isolated from the outside chamber So means that the compressed air Acom in the outside chamber So does not flow directly into the cooling air chamber Sa. As described above, the cooling air jacket 65 is in contact with the mounting flange 66, which is provided at the end on the downstream side Dcd of the pipe 51, meaning that the cooling air jacket 65 is located on the downstream side Dcd of the acoustic cover 62. The cooling air branch lines 74 of the cooling device 70 described above are connected to the cooling air jacket 65. Therefore, the amplified cooling air Acl flows from the cooling device 70 into the cooling air chamber Sa.

[0053] As in Fig. 3 and Fig. As shown in Figure 4, the tube 51 contains several acoustic holes 59, several first airflow paths 56 and several third airflow paths 58. Fig. Figure 3 is a sectional view of a main part of the transition piece 50 along a virtual plane containing the combustion chamber axis Lcom, and Fig. 4 is a view of arrow IV in Fig. 3.

[0054] The acoustic hole 59 penetrates the plate forming the tube 51 from the acoustic space Ss to the combustion chamber Sc. Therefore, the acoustic hole 59 is a hole that penetrates a section of the tube 51, which is covered by the acoustic cover 62, from the outer circumferential surface 55o to the inner circumferential surface 55i of the tube 51.

[0055] Both the first airflow path 56 and the third airflow path 58 are formed between the outer circumferential surface 55o and the inner circumferential surface 55i of the pipe 51. The first airflow path 56 includes an inlet 56i facing the cooling air space Sa, which directs the air in the cooling air space Sa into the first airflow path 56, and an outlet 56o facing the acoustic space Ss, which directs the air that has passed through the first airflow path 56 into the acoustic space Ss. Therefore, the inlet 56i of the first airflow path 56 is formed in a section of the outer circumferential surface 55o of the pipe 51, with the section being covered by the cooling air jacket 65. Furthermore, the outlet 56o of the first airflow path 56 is formed in a section of the outer circumferential surface 55o of the tube 51, the section being covered by the acoustic cover 62.The third airflow path 58 includes an inlet 58i facing the cooling air space Sa, which directs the air in the cooling air space Sa into the third airflow path 58, and an outlet 58o facing the outside space So, which directs the air that has passed through the third airflow path 58 into the outside space So. Therefore, the inlet 58i of the third airflow path 58 is formed in a section of the outer circumferential surface 55o of the pipe 51, the section being covered by the cooling air jacket 65. Furthermore, the outlet 58o of the third airflow path 58 is formed in a section of the outer circumferential surface 55o of the pipe 51, the section being not covered by the acoustic cover 62 and the cooling air jacket 65.Among the several third airflow paths 58, the outlets 58o of some of the third airflow paths 58 are formed in a section on the upstream side Dcu of the outer circumferential surface 55o of the tube 51 in relation to the section covered by the acoustic cover 62.

[0056] As in Fig. As shown in Figure 5, the plate forming the tube 51 is formed by joining an outer circumferential wall plate 52o and an inner circumferential wall plate 52i by soldering or the like. Several grooves 53, which are recessed in one direction away from the other side and which are long in the axial direction Dcom, are formed in a wall plate consisting of the outer circumferential wall plate 52o and the inner circumferential wall plate 52i. An airflow path 56 (58), through which the air flows, is formed between an inner surface of the groove 53 and a surface of the other wall plate. In the present embodiment, the grooves 53 are formed in the outer circumferential wall plate 52o.

[0057] Next, the operation of the gas turbine 10 described above will be described.

[0058] Compressor 20 draws in ambient air A and compresses it as it passes through the air compression flow path. The compressed air, namely compressed air Acom, flows from the air compression flow path of compressor 20 into the intermediate housing 16. The compressed air Acom is fed via the fuel nozzle 41 of the combustion chamber 40 into the pipe 51 of the transition piece 50. The fuel F is injected by the multiple burners 42 of the fuel nozzle 41 into the pipe 51 of the transition piece 50. The fuel F is burned in the compressed air Acom that has been fed into the combustion chamber Sc of the pipe 51. As a result of combustion, the combustion gas G is produced, and the combustion gas G flows from the transition piece 50 into the combustion gas flow path of the turbine 30. As the combustion gas G passes through the combustion gas flow path, the turbine rotor 31 rotates.

[0059] While the fuel F is burned in the combustion chamber Sc, the booster compressor 76 of the cooling device 70 is driven. As a result, a portion of the compressed air Acom in the external chamber So, or in other words, a portion of the compressed air Acom in the intermediate housing 16, is vented from inside the intermediate housing 16, flows into the cooler 75 of the cooling device 70, and is then cooled there. The compressed air Acom, cooled in the cooler 75, is boosted by the booster compressor 76 and then flows as the boosted cooling air Acl into the cooling air chamber Sa of the transition piece 50. Since the boosted cooling air Acl is air obtained by cooling and then boosting the compressed air Acom in the intermediate housing 16, the boosted cooling air Acl has a lower temperature and a higher pressure than that of the compressed air Acom in the intermediate housing 16.

[0060] The enhanced cooling air Acl in the cooling air space Sa flows into the first airflow path 56 and the third airflow path 58 of the pipe 51, in order to flow through the airflow paths 56 and 58. As it flows through the airflow paths 56 and 58, the enhanced cooling air Acl is heated due to heat exchange with the pipe 51, which is exposed to the high-temperature combustion gas G, while simultaneously cooling the pipe 51.

[0061] The enhanced cooling air Acl, which has passed through the third airflow path 58, flows from the outlet 58o of the third airflow path 58 into the outside chamber So and mixes with the compressed air Acom present in the outside chamber So. Furthermore, the enhanced cooling air Acl, which has passed through the first airflow path 56, flows from the outlet 56o of the first airflow path 56 into the acoustic chamber Ss. The enhanced cooling air Acl flowing into the acoustic chamber Ss flows from the acoustic hole 59 into the combustion chamber Sc. Therefore, the combustion gas G in the combustion chamber Sc does not flow into the acoustic chamber Ss.

[0062] To ensure that the combustion gas G in the combustion chamber Sc does not flow into the acoustic space Ss, a pressure Ps in the acoustic space Ss must be higher than a pressure Pc in the combustion chamber Sc, and a pressure difference ΔP between the two pressures (= Ps - Pc > 0) must be a certain value or more.

[0063] The pressure difference ΔP is proportional to the density p of a fluid and is proportional to the square of the flow velocity v of the fluid, as expressed by the following equation. ΔP∝ρ⋅v2

[0064] As can be seen from the equation above, increasing the flow velocity v of the fluid is more effective than increasing the density ρ of the fluid if the pressure difference ΔP is to be set to a certain value or higher. Furthermore, the flow velocity v of a fluid is increased by increasing the fluid's volume while simultaneously decreasing its density ρ, thus suppressing the mass flow rate of the fluid flowing from the acoustic chamber Ss to the combustion chamber Sc. One method for increasing the fluid's volume and simultaneously decreasing its density ρ involves expanding the fluid by increasing the amount of heat it receives.

[0065] To facilitate understanding of the following description, a comparative example of this aspect is described here. One pipe in the comparative example does not contain the first airflow path 56, but contains a second airflow path 57, which is defined by an imaginary line (alternating long and twice short dashed line) in Fig. Figure 3 shows the second airflow path 57, which is formed between the outer circumferential surface 55o and the inner circumferential surface 55i of the pipe 51. The second airflow path 57 includes an inlet 57i facing the outer space So, which directs the air in the outer space So into the second airflow path 57, and an outlet 57o facing the acoustic space Ss, which directs the air that has passed through the second airflow path 57 into the acoustic space Ss. The inlet 57i of the second airflow path 57 is located on the upstream side Dcu of the acoustic cover 62. The air in the outer space So flows from the inlet 57i of the second airflow path 57 into the second airflow path 57, in order to flow through the second airflow path 57. During the passage through the second airflow path 57, the air is heated due to heat exchange with the tube 51, which is exposed to the combustion gas G, while it cools the tube 51.The air that has passed through the second airflow path 57 flows from the outlet 57o of the second airflow path 57 into the acoustic space Ss. The air flowing into the acoustic space Ss flows from the acoustic hole 59 to the combustion chamber Sc.

[0066] In the comparative example, if the air in the outside space So, namely the compressed air Acom, has a constant pressure and a constant temperature, one method for increasing the amount of heat transferred to the air flowing through the second airflow path 57 is, for example, a method for lengthening the flow path length of the second airflow path 57. The following problems arise with this method. (1) There is a possibility that the pressure loss in the second airflow path 57 increases, so that the air in the outside space So does not reach the acoustic space Ss or does not flow out from the acoustic hole 59 to the combustion chamber Sc. (2) There is a possibility that the temperature of the air will become very high by the time the air reaches the acoustic space Ss, so that the air will not be able to cool the tube 51.

[0067] Furthermore, there is another method for forming the second airflow path 57 in a region of the tube 51 that is slightly heated by the combustion gas G. Even with this method, the problem (2) described above occurs.

[0068] In the present embodiment, the enhanced cooling air Acl flows through the first airflow path 56 in the cooling air chamber Sa, which is isolated from the outside chamber So. Therefore, in the present embodiment, the air with a pressure and temperature that differ from those of the compressed air Acom in the outside chamber So is able to flow through the first airflow path 56. Thus, in the present embodiment, the enhanced cooling air Acl flows through the first airflow path 56 at a higher pressure and a lower temperature than that of the compressed air Acom in the outside chamber So.For this reason, in the present embodiment, the above problems (1) and (2) do not occur, even when the method for extending the flow path length of the first air flow path 56 and / or the method for forming the first air flow path 56 in a region of the tube 51 which is slightly heated by the combustion gas G is used.

[0069] 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 chamber Sc is set to a certain value or more, so that, while allowing air to flow from the acoustic space Ss to the combustion chamber Sc on the inner circumferential side of the tube 51, the mass flow rate of the air can be suppressed.

[0070] As described above, in the present embodiment, since the mass flow rate of the air flowing from the acoustic chamber Ss to the combustion chamber Sc on the inner circumferential side of the tube 51 can be suppressed, the amount of NOx produced can be suppressed. Furthermore, in the present embodiment, since the amount of combustion gas G that is diluted by the air flowing out to the combustion chamber Sc is reduced, a reduction in the temperature of the gas supplied to the turbine 30 can be suppressed, and a reduction in the efficiency of the gas turbine 10 can be suppressed.

[0071] In the present embodiment, the method for increasing the amount of air heated comprises the method for lengthening the flow path length of the first airflow path 56 and the method for forming the first airflow path 56 in a region of the pipe 51 that is slightly heated by the combustion gas G. In particular, in the present embodiment, the flow path length of the first airflow path 56 is lengthened by providing the cooling air jacket 65 in a section on the downstream side Dcd of the pipe 51 and by allowing the cooling air space Sa in the cooling air jacket 65 and the acoustic space Ss in the acoustic damper 61, which is arranged in a section on the upstream side Dcu of the pipe 51, to communicate with each other via the first airflow path 56.In the combustion chamber Sc of the tube 51, the temperature on the downstream side Dcd of a peak section of a flame formed by the combustion of the fuel F is higher than the temperature on the upstream side Dcu of the peak section of the flame. Therefore, a region on the downstream side Dcd of the tube 51 is heated more readily by the combustion gas G than a region on the upstream side Dcu. Therefore, in the present embodiment, the first airflow path 56 is formed in a region on the downstream side Dcd of the tube 51 that is heated more readily.

[0072] In the present embodiment, as described above, the method for increasing the amount of air heated employs both the method for lengthening the flow path length of the first airflow path 56 and the method for forming the first airflow path 56 in a region of the tube 51 that is slightly heated by the combustion gas G. However, only one of the two methods above can also be used. [Second embodiment]

[0073] A second embodiment of the gas turbine equipment according to the present invention is described below with reference to Fig. 6 and Fig. 7 described. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the first embodiment only in the configuration of the combustion chamber transition piece. Therefore, mainly one configuration of a transition piece 50a of the present embodiment is described below.

[0074] Similar to the first embodiment, the transition piece 50a of the present embodiment includes a tube 51a; the acoustic damper 61; the cooling air jacket 65; and the mounting flange 66. Similar to the tube 51 of the first embodiment, the tube 51a includes the inlet opening 54i; the outlet opening 54o; the outer circumferential surface 55o; the inner circumferential surface 55i; several of the first airflow paths 56; and several of the third airflow paths 58. The tube 51a of the present embodiment further includes several of the second airflow paths 57. The second airflow path 57 is formed between the outer circumferential surface 55o and the inner circumferential surface 55i of the tube 51a.The second airflow path 57 includes the inlet 57i, which faces the outside space So and directs the compressed air Acom in the outside space So into the second airflow path 57, and the outlet 57o, which faces the acoustic space Ss and directs the compressed air Acom, which has passed through the second airflow path 57, into the acoustic space Ss. The inlet 57i of the second airflow path 57 is located on the upstream side Dcu of the acoustic cover 62. The pipe 51a of the present embodiment contains the third airflow path 58, but need not contain the third airflow path 58.

[0075] In the present embodiment, as in the first embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first airflow path 56 and the third airflow path 58 of the pipe 51a, in order to flow through the airflow paths 56 and 58. As it flows through the airflow paths 56 and 58, the enhanced cooling air Acl is heated due to heat exchange with the pipe 51a, which is exposed to the high-temperature combustion gas G, while simultaneously cooling the pipe 51a. The enhanced cooling air Acl, having passed through the third airflow path 58, flows from the outlet 58o of the third airflow path 58 to the outside space So and mixes with the compressed air Acom present in the outside space So. Furthermore, the enhanced cooling air Acl, which has passed through the first airflow path 56, flows from the outlet 56o of the first airflow path 56 into the acoustic space Ss.

[0076] The compressed air Acom in the external space So flows from the inlet 57i of the second airflow path 57 into the second airflow path 57, in order to flow through the second airflow path 57. During its passage through the second airflow path 57, the compressed air Acom is heated due to heat exchange with the pipe 51a, which is exposed to the combustion gas G, while simultaneously cooling the pipe 51a. The compressed air Acom, having passed through the second airflow path 57, flows from the outlet 57o of the second airflow path 57 into the acoustic space Ss.

[0077] Therefore, in the present embodiment, the enhanced cooling air Acl, which has flowed through the first airflow path 56, and the compressed air Acom, which has flowed through the second airflow path 57, flow into the acoustic chamber Ss. The air flowing into the acoustic chamber Ss flows out through the acoustic hole 59 to the combustion chamber Sc. As described above, in the present embodiment, similar to the first embodiment, the air with a large amount of heat is able to flow out to the combustion chamber Sc, since the air flowing from the acoustic chamber Ss through the acoustic hole 59 to the combustion chamber Sc contains the enhanced cooling air Acl that has flowed through the first airflow path 56.Therefore, in the present embodiment, similar to the first embodiment, the mass flow rate of the air can be suppressed, while allowing the air to flow from the acoustic space Ss to the combustion chamber Sc.

[0078] In the first embodiment, a section on the upstream side Dcu of the pipe 51 with respect to the acoustic cover 62 is cooled by the air flowing through the third airflow path 58. The amount of heat transferred to the air flowing through the third airflow path 58 up to the point at which it reaches the acoustic cover 62 is substantial. In contrast, in the present embodiment, the section on the upstream side Dcu of the pipe 51a with respect to the acoustic cover 62 is cooled by the air flowing through the second airflow path 57. In the section on the upstream side Dcu of the pipe 51a with respect to the acoustic cover 62, the temperature of the air flowing through the second airflow path 57 is lower than the temperature of the air flowing through the third airflow path 58.For this reason, in the present embodiment the cooling capacity of the section on the upstream side Dcu of the pipe 51a with respect to the acoustic cover 62 can be increased more than in the first embodiment. [Third embodiment]

[0079] A third embodiment of the gas turbine equipment according to the present invention is described below with reference to Fig. 8 and Fig. 9 described. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the first embodiment only in the configuration of the combustion chamber transition piece. Therefore, mainly one configuration of a transition piece 50b of the present embodiment is described below.

[0080] Similar to the first embodiment, the transition piece 50b of the present embodiment includes a pipe 51b; acoustic dampers 61a and 61b; the cooling air jacket 65; and the mounting flange 66. However, the transition piece 50b of the present embodiment includes several of the acoustic dampers 61a and 61b. Similar to the pipe 51 of the first embodiment, the pipe 51b includes the inlet opening 54i; the outlet opening 54o; the outer circumferential surface 55o; the inner circumferential surface 55i; several of the first airflow paths 56; and several of the third airflow paths 58. The outlet 56o of the first airflow path 56 of the present embodiment faces only one first acoustic chamber Ssa of the first acoustic damper 61a of the several acoustic dampers 61a and 61b and does not face a second acoustic chamber Ssb of the second acoustic damper 61b.Therefore, in the present embodiment, the enhanced cooling air Acl in the cooling air space Sa flows through the first airflow path 56 into the first acoustic space Ssa, but does not flow into the second acoustic space Ssb. The pipe 51b of the present embodiment further contains several of the second airflow paths 57. The second airflow path 57 is formed between the outer circumferential surface 55o and the inner circumferential surface 55i of the pipe 51b. The second airflow path 57 includes the inlet 57i, which faces the outer space So and directs the air in the outer space So into the second airflow path 57, and the outlet 57o, which faces only the second acoustic space Ssb and directs the air that has passed through the second airflow path 57 into the second acoustic space Ssb.Therefore, in the present embodiment, the compressed air Acom in the external space So flows through the second airflow path 57 into the second acoustic space Ssb, but does not flow into the first acoustic space Ssa. The inlet 57i of the second airflow path 57 is located on the upstream side Dcu of the respective acoustic covers 62 of the multiple acoustic dampers 61a and 61b. The pipe 51b of the present embodiment contains the third airflow path 58, but need not contain the third airflow path 58.

[0081] In the present embodiment, as in the first embodiment, the enhanced cooling air Acl in the cooling air space Sa flows into the first airflow path 56 and the third airflow path 58 of the pipe 51b, in order to flow through the airflow paths 56 and 58. As it flows through the airflow paths 56 and 58, the enhanced cooling air Acl is heated by heat exchange with the pipe 51b, which is exposed to the high-temperature combustion gas G, while simultaneously cooling the pipe 51b. The air that has passed through the third airflow path 58 flows from the outlet 58o of the third airflow path 58 to the outside space So and mixes with the compressed air Acom present in the outside space So. Furthermore, the enhanced cooling air Acl, which has passed through the first airflow path 56, flows from the outlet 56o of the first airflow path 56 into the first acoustic space Ssa.The air that has flowed into the first acoustic chamber Ssa flows from a first acoustic hole 59a of the first acoustic damper 61a to the combustion chamber Sc.

[0082] The compressed air Acom in the external chamber So flows from the inlet 57i of the second airflow path 57 into the second airflow path 57, in order to flow through the second airflow path 57. During its passage through the second airflow path 57, the compressed air Acom is heated due to heat exchange with the tube 51b, which is exposed to the combustion gas G, while simultaneously cooling the tube 51b. The compressed air Acom, having passed through the second airflow path 57, flows from the outlet 57o of the second airflow path 57 into the second acoustic chamber Ssb. The compressed air Acom, having flowed into the second acoustic chamber Ssb, flows out of a second acoustic hole 59b of the second acoustic damper 61b into the combustion chamber Sc.

[0083] As described above, in the present embodiment, the enhanced cooling air Acl, which has flowed through the first airflow path 56, flows into the first acoustic chamber Ssa of several acoustic chambers Ss. The air flowing into the first acoustic chamber Ssa flows out through the first acoustic opening 59a to the combustion chamber Sc. For this reason, in the present embodiment, the total mass flow rate of the air flowing out of all acoustic chambers Ssa and Ssb to the combustion chamber Sc can be suppressed more effectively than if only the compressed air Acom, which has flowed through the second airflow path 57, flows into all acoustic chambers Ssa and Ssb.

[0084] Furthermore, in the present embodiment, similar to the second embodiment, the cooling capacity of the section on the upstream side Dcu of the pipe 51b with respect to the acoustic cover 62 can be increased more than in the first embodiment, since the second airflow path 57 is provided. [Fourth embodiment]

[0085] A fourth embodiment of the gas turbine equipment according to the present invention is described below with reference to Fig. 10 and Fig. 11. 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 combustion chamber transition piece. Therefore, mainly one configuration of a transition piece 50c of the present embodiment is described below.

[0086] Similar to the third embodiment, the transition piece 50c of the present embodiment includes a tube 51c; several of the acoustic dampers 61a and 61b; the cooling air jacket 65; and the mounting flange 66. Similar to the tube 51b of the third embodiment, the tube 51c includes the inlet opening 54i; the outlet opening 54o; the outer circumferential surface 55o; the inner circumferential surface 55i; several of the first airflow paths 56; and several of the second airflow paths 57. In the present embodiment, among the several first airflow paths 56, the outlets 56o of some of the first airflow paths 56 face only the first acoustic space Ssa of the first acoustic damper 61a of the several acoustic dampers 61a and 61b and do not face the second acoustic space Ssb of the second acoustic damper 61b.Furthermore, among the multiple first airflow paths 56, the outlets 56o of the other first airflow paths 56 are only directed towards the second acoustic chamber Ssb of the second acoustic damper 61b of the multiple acoustic dampers 61a and 61b and are not directed towards the first acoustic chamber Ssa of the first acoustic damper 61a. Therefore, in the present embodiment, the amplified cooling air Acl in the cooling air chamber Sa flows through one of the multiple first airflow paths 56 into each of the acoustic chambers Ssa and Ssb of the multiple acoustic dampers 61a and 61b. In the present embodiment, among the several second airflow paths 57, the outlets 57o of some of the second airflow paths 57 are only directed towards the first acoustic space Ssa of the first acoustic damper 61a of the several acoustic dampers 61a and 61b and are not directed towards the second acoustic space Ssb of the second acoustic damper 61b.Furthermore, among the multiple secondary airflow paths 57, the outlets 57o of the other secondary airflow paths 57 are only directed towards the second acoustic chamber Ssb of the second acoustic damper 61b of the multiple acoustic dampers 61a and 61b and are not directed towards the first acoustic chamber Ssa of the first acoustic damper 61a. Therefore, in the present embodiment, the compressed air Acom in the external chamber So flows through one of the multiple secondary airflow paths 57 into each of the acoustic chambers Ssa and Ssb of the multiple acoustic dampers 61a and 61b.

[0087] As described above, in the present embodiment, similar to the second embodiment, the enhanced cooling air Acl, which has flowed through the first airflow path 56, and the compressed air Acom, which has flowed through the second airflow path 57, flow accordingly into the acoustic chambers Ssa and Ssb of the multiple acoustic dampers 61a and 61b. The air flowing into the first acoustic chamber Ssa flows out through the first acoustic hole 59a to the combustion chamber Sc. The air flowing into the second acoustic chamber Ssb flows out through the second acoustic hole 59b to the combustion chamber Sc. Therefore, in the present embodiment, as in the second embodiment, the mass flow rate of the air can be suppressed, while the air is allowed to flow from the acoustic chambers Ssa and Ssb to the combustion chamber Sc on the inner circumferential side of the tube 51c.

[0088] The pipe 51c of the present embodiment does not contain the third airflow path 58 in any of the above embodiments. However, the pipe 51c of the present embodiment may contain the third airflow path 58. [Fifth embodiment]

[0089] A fifth embodiment of the gas turbine equipment according to the present invention is described below with reference to Fig. 12 and Fig. 13. The gas turbine equipment of the present embodiment differs from the gas turbine equipment of the second embodiment only in the configuration of the combustion chamber transition piece. Therefore, mainly one configuration of a transition piece 50d of the present embodiment is described below.

[0090] Similar to the second embodiment, the transition piece 50d of the present embodiment includes the tube 51a; the acoustic damper 61; the cooling air jacket 65; and the mounting flange 66. Similar to the tube 51a of the second embodiment, the tube 51a includes the inlet opening 54i; the outlet opening 54o; the outer circumferential surface 55o; the inner circumferential surface 55i; several of the first airflow paths 56; and several of the third airflow paths 58. The tube 51a of the present embodiment further includes several of the second airflow paths 57. The tube 51a of the present embodiment includes the third airflow path 58, but need not include the third airflow path 58.

[0091] In the present embodiment, as in the second embodiment, the enhanced cooling air Acl flows in the cooling air space Sa into the first airflow path 56 and the third airflow path 58 of the pipe 51a and flows through the airflow paths 56 and 58. During its passage through the airflow paths 56 and 58, the enhanced cooling air Acl is heated due to heat exchange with the pipe 51a, which is exposed to the high-temperature combustion gas G, while simultaneously cooling the pipe 51a. The enhanced cooling air Acl, having passed through the third airflow path 58, flows from the outlet 58o of the third airflow path 58 to the outside space So and mixes with the compressed air Acom present in the outside space So. Furthermore, the enhanced cooling air Acl, which has passed through the first airflow path 56, flows from an outlet 156o of the first airflow path 56 into the acoustic space Ss.

[0092] The compressed air Acom in the external space So flows from the inlet 57i of the second airflow path 57 into the second airflow path 57, in order to flow through the second airflow path 57. During its passage through the second airflow path 57, the compressed air Acom is heated due to heat exchange with the pipe 51a, which is exposed to the combustion gas G, while simultaneously cooling the pipe 51a. The compressed air Acom, having passed through the second airflow path 57, flows from the outlet 57o of the second airflow path 57 into the acoustic space Ss.

[0093] Therefore, in the present embodiment, the enhanced cooling air Acl, which has flowed through the first airflow path 56, and the compressed air Acom, which has flowed through the second airflow path 57, flow from the outlet 156o and the outlet 57o, respectively, into the acoustic chamber Ss. The air flowing into the acoustic chamber Ss flows out through the acoustic hole 59 to the combustion chamber Sc. As described above, in the present embodiment, similar to the first embodiment, the air with a large amount of heat is able to flow out to the combustion chamber Sc, since the air flowing from the acoustic chamber Ss through the acoustic hole 59 to the combustion chamber Sc contains the enhanced cooling air Acl that has flowed through the first airflow path 56.Therefore, in the present embodiment, similar to the second embodiment, the mass flow rate of the air can be suppressed, while allowing the air to flow from the acoustic space Ss to the combustion chamber Sc.

[0094] In the second embodiment described above, the opening area of ​​outlet 56o and outlet 57o is equal; however, in the present embodiment, the opening area of ​​outlet 156o, which directs the enhanced cooling air Acl, which has passed through the first airflow path 56, into the acoustic space Ss, is larger than the opening area of ​​outlet 57o, which directs the compressed air Acom, which has passed through the second airflow path 57, into the acoustic space Ss. Therefore, in the present embodiment, the flow velocity of the enhanced cooling air Acl flowing from outlet 156o into the acoustic space Ss can be lower than the flow velocity of the enhanced cooling air Acl flowing from outlet 56o into the acoustic space Ss in the second embodiment.Since a reduction in static pressure in the acoustic space Ss can be suppressed due to the inflow of the enhanced cooling air Acl, the combustion gas G in the combustion chamber Sc can be prevented from flowing through the acoustic hole 59 into the acoustic space Ss to a greater extent than in the second embodiment. Furthermore, in the present embodiment, because the opening area of ​​the outlet 1560 of the first airflow path 56, which allows a larger mass flow rate than the second airflow path 57, is large, a reduction in static pressure in the acoustic space Ss can be efficiently suppressed. [Modification example of fifth embodiment]

[0095] In the fifth embodiment described above, the case was presented in which the outlet 156o, which has a larger opening area than that of the outlet 57o, is formed in the tube 51. In other words, the fifth embodiment described the case in which an outlet 156o is provided in a first airflow path 56. However, as in Fig.Figure 14 shows that several (for example, two) outlets 256o, facing the acoustic space Ss, are provided in a first airflow path 56. The total opening area of ​​the several outlets 256o provided in a first airflow path 56 is larger than the opening area of ​​a single outlet 57o. In such a modification example of the fifth embodiment, similar to the fifth embodiment, the combustion gas G can be prevented from flowing into the acoustic space Ss by reducing the flow velocity of the enhanced cooling air Acl flowing into the acoustic space Ss.

[0096] Furthermore, instead of the outlet 56o of the third and fourth embodiments, the outlet 156o of the fifth embodiment or the outlets 256o of the modification example of the fifth embodiment can be provided. Industrial applicability

[0097] According to one aspect of the present invention, while allowing air to flow from the acoustic space of the acoustic damper to the space on the inner circumferential side of the tube, the mass flow rate of the air can be suppressed. Reference symbol list 10 Gas turbine 11 Gas turbine rotor 15 gas turbine casings 16 intermediate housings 20 Compressor 21 Compressor rotor 22 Rotor shaft 23 rotor blade rows 25 Compressor housings 26 stator blade row 30 Turbine 31 Turbine rotor 32 Rotor shaft 33 rotor blade row 35 turbine housings 36 stator blade rows 40 combustion chamber 41 Fuel nozzle 42 burners 43 frames 45 Fuel line 46 Fuel Flow Rate Control Valve 50, 50a, 50b, 50c, 50d Transition piece (or combustion tube) 51, 51a, 51b, 51c pipe 52i inner perimeter wall panel 520 Outer perimeter wall panel 53 Nut 54i Inlet opening 540 Outlet opening 55i inner circumference area 550° external perimeter 56 first airflow path 56i Inlet 56°, 156°, 256° outlet 57 second airflow path 57 Admission 57o outlet 58 third airflow path 58i Inlet 58° outlet 59 acoustic hole 59a first acoustic hole 59b second acoustic hole 61 acoustic damper 61a first acoustic damper 61b second acoustic damper 62 Acoustic cover 65 Cooling air jacket 66 Mounting flange 70 Cooling device 71 Cooling air duct 72 Vent line 73 Main cooling air line 74 Cooling air branch line 75 coolers 76 Booster compressor A air Acom compressed air ACL enhanced cooling air G Combustion gas Lcom combustion chamber axis (or simply axis) Lr rotor axis Since rotor axial direction Dau axial upstream side Dad axial downstream side DC circumferential direction Dr. Radial direction Three radial inner sides Dro radial outer side Dcom combustion chamber axial direction (or simply axial direction) Dcu combustion chamber upstream side (or simply upstream side) DCD combustion chamber downstream side (or simply downstream side) Sc combustion chamber Ss acoustic space Ssa first acoustic space SSB second acoustic space Sa cooling air space So outdoor space QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] JP 2019097550

[0002]

Claims

[1] Transition piece, comprising: a pipe that has a tubular shape around an axis and in which fuel is burned on an inner circumferential side of the pipe; an acoustic damper comprising part of a plate forming the tube and an acoustic cover which, together with that part of the plate, forms an acoustic space on an outer circumferential side of the tube; and a cooling air jacket which, together with another part of the plate forming the tube, with the exception of a section forming the acoustic damper, forms a cooling air space, wherein the cooling air space is isolated from an external space which is a space on the outer circumferential side of the tube, the pipe contains an inlet opening formed at one end on an upstream side, which is a side in an axial direction in which the axis extends, an outlet opening formed at one end on a downstream side, which is the other side in the axial direction, an outer circumferential surface facing the outer perimeter side, an inner circumferential surface facing the inner circumferential side, a first airflow path formed between the outer circumferential surface and the inner circumferential surface, and an acoustic hole that penetrates the pipe from the acoustic space to a combustion chamber, which is a space on the inner circumferential side of the pipe, and The first airflow path includes an inlet facing the cooling air space, which directs air from the cooling air space into the first airflow path, and an outlet facing the acoustic space, which directs the air that has passed through the first airflow path into the acoustic space. [2] Transition piece according to claim 1, the cooling air jacket is located on the downstream side of the acoustic cover. [3] Transition piece according to claim 2, further comprising: a mounting flange extending from the outer circumferential surface of the pipe to the outer circumferential side at the end on the downstream side of the pipe, where the cooling air jacket is in contact with the mounting flange. [4] Transition piece according to any one of claims 1 to 3, wherein the pipe contains a second airflow path formed between the outer circumferential surface and the inner circumferential surface, and The second airflow path includes an inlet facing the outside space, which directs air from the outside space into the second airflow path, and an outlet facing the acoustic space, which directs the air that has passed through the second airflow path into the acoustic space. [5] Transition piece according to any one of claims 1 to 3, further comprising: several of the acoustic covers, wherein the outlet of the first airflow path faces the acoustic space formed by at least one of the several acoustic covers. [6] Transition piece according to claim 5, wherein the pipe contains a second airflow path formed between the outer circumferential surface and the inner circumferential surface, and The second airflow path includes an inlet facing the outside space, which directs air from the outside space into the second airflow path, and an outlet facing the acoustic space, which is formed by at least one of the several acoustic covers, and which directs the air that has passed through the second airflow path into the acoustic space. [7] Transition piece according to claim 6, wherein the pipe for each of the multiple acoustic covers contains the first airflow path and the second airflow path, which communicate with the acoustic space formed by each of the acoustic covers. [8] Transition piece according to one of claims 4, 6 and 7, wherein the inlet of the second airflow path is arranged on the upstream side of the acoustic cover. [9] Transition piece according to any one of claims 1 to 8, wherein the pipe includes a third airflow path formed between the outer circumferential surface and the inner circumferential surface, and The third airflow path includes an inlet facing the cooling air space, which directs the air in the cooling air space into the third airflow path, and an outlet facing the outside space, which directs the air that has passed through the third airflow path into the outside space. [10] Transition piece according to claim 4, wherein an opening area of ​​the outlet that directs the air that has passed through the first airflow path into the acoustic space is larger than an opening area of ​​the outlet that directs the air that has passed through the second airflow path into the acoustic space. [11] Combustion chamber, comprising: the transition piece according to any one of claims 1 to 10; and a burner that injects fuel and air into the combustion chamber. [12] Gas turbine, comprising: the combustion chamber according to claim 11; a compressor; a turbine; and an intermediate housing wherein the compressor includes a compressor rotor that rotates around a rotor axis and a compressor housing that covers the compressor rotor, The turbine includes a turbine rotor that rotates integrally with the compressor rotor around the rotor axis, and a turbine housing that covers the turbine rotor. the intermediate housing is arranged in a rotor axial direction between the compressor housing and the turbine housing, in which the rotor axis extends, and connects the compressor housing and the turbine housing, and compressed air that has been delivered by the compressor flows into the intermediate housing, and the combustion chamber is provided in the intermediate housing. [13] Gas turbine equipment, comprising: the gas turbine according to claim 12; a cooling air duct that carries the compressed air in the intermediate case to an outside of the intermediate case and then carries the compressed air into the cooling air jacket; a cooler that is provided in the cooling air duct and cools the compressed air passing through the cooling air duct; and a booster compressor that is provided in the cooling air duct and boosts the compressed air that has been cooled by the radiator.