JP2017133788A - Acoustic damper, combustor and gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To suppress deterioration in strength of a passage which forms an acoustic part.SOLUTION: An acoustic damper 1 which is fixed to a vibration generating source and which is provided along an outside surface of the vibration generating source includes an acoustic part N which forms a series of passages 3 having an inlet 3A which takes in air vibration generating in the vibration generating source, and a terminal end 3B which serves as resistance of the air vibration by blocking the downstream side of propagation of the air vibration. In the acoustic part N, the passages 3 are folded and the plurality of passages 3 are arranged adjacent to each other around the terminal end, and also, the inlet 3A and the terminal end 3B of the series of passages 3 are arranged separately.SELECTED DRAWING: Figure 4

Description

  The present invention relates to an acoustic damper, a combustor, and a gas turbine.

  Conventionally, for example, in Patent Document 1, in order to improve damping performance and maintainability, an acoustic liner having an acoustic liner resonance space composed of a perforated plate and a housing, and an acoustic liner resonance space connected to the housing and inside thereof An attenuation device is disclosed that includes an acoustic damper having an acoustic damper resonance space in communication with the acoustic damper. In this damping device, an acoustic liner is attached around the tail cylinder of the combustor, and an acoustic damper is provided along the extending direction of the tail cylinder.

  Conventionally, for example, in Patent Document 2, an acoustic unit having an acoustic damper resonance space of an acoustic damper has an internal combustion region in order to reduce the mounting space of the acoustic damper to reduce the size and improve maintenance. It is folded at least once along the cylinder to be formed.

  Conventionally, for example, in Patent Document 3, in order to reduce vibrations in a wide frequency band, an acoustic damper having a passage (pipe) having an opening and providing a resistance to a fluid flowing through the passage. Is disclosed. In this acoustic damper, a passage and a resistor, which are refracted and reduced in size, are attached to a bypass pipe attached to a combustion cylinder of a combustor, and the inside of the bypass pipe and the passage form an opening of the passage. It is communicated through.

JP 2006-266671 A Japanese Patent No. 5291790 JP 2006-22966 A

  In each of Patent Documents 1, 2, and 3 described above, the acoustic unit is one in which one end of a passage forming the acoustic liner resonance space is an inlet for taking in air vibration from a vibration generation source such as a combustion cylinder, and the other end is terminated. In this way, a pressure fluctuation is generated in the passage where the pressure gradually increases from the inlet toward the terminal.

  In such a structure, in patent document 1 and patent document 2, it appears in the table so that each side of the terminal portion of the passage which is an acoustic unit is in contact with the air which is not vibrating. The pressure fluctuation of the non-vibrating air is almost 0 kPa. On the other hand, when air fluctuation is taken in from the vibration generation source and the pressure fluctuation at the end resonated in the acoustic tube is 100 kPa, for example, each side of the end portion near 100 kPa. Since the direction is adjacent to 0 kPa, there is a possibility that a large stress is applied due to the pressure difference and the strength is lowered.

  In Patent Document 3, the first layer having an inlet that takes in air vibration from a vibration source and the second layer having a terminal end form one passage. The first layer is formed in a spiral shape from the inside to the outside with the inlet at the center, and the second layer is formed in a spiral shape from the outside to the inside with the terminal end in the center. Yes. In such a configuration, the inlet and the end are arranged adjacent to each other, and a large stress is applied due to the pressure difference between them, and the strength may be reduced.

  This invention solves the subject mentioned above, and aims at providing the acoustic damper, combustor, and gas turbine which can suppress the intensity | strength fall of the channel | path which makes an acoustic part.

  In order to achieve the above-described object, the acoustic damper according to the present invention is an acoustic damper that is fixed to a vibration generation source and provided along the outer surface of the vibration generation source, the air vibration generated at the vibration generation source. And an acoustic part that forms a series of passages having an inlet that closes the downstream side of the propagation of the air vibrations and that serves as a resistance to the air vibrations, and the acoustic part has the passages folded back A plurality of the passages are arranged adjacent to each other around the end portion, and the entrance and the end of the series of the passages are spaced apart from each other.

  According to this acoustic damper, since the periphery of the end portion where the pressure is high is sandwiched between the passages in the acoustic portion, the pressure difference between the end portion and the periphery is reduced, and the stress on the end portion is reduced. To do. As a result, it is possible to suppress a decrease in strength of the terminal portion. In addition, since the entrance and the end of the passage of the acoustic unit are spaced apart from each other, these pressure differences do not occur, and a decrease in strength of the acoustic unit can be suppressed.

  Further, the acoustic damper of the present invention includes a plurality of the acoustic parts forming the series of the passages, and is adjacent to the periphery of the end portion of the passage of each of the acoustic parts. The passages of the acoustic units are arranged, and the entrance and the terminal end of the passages of the acoustic units are arranged apart from each other.

  According to this acoustic damper, since the periphery of the terminal portion having a large pressure in the passages of the plurality of acoustic parts is disposed between the own passage and the passages of the other acoustic parts, A pressure difference becomes small and the stress concerning a termination | terminus part falls. As a result, it is possible to suppress a decrease in strength of the terminal portion. In addition, since the entrance and the end of the passage of the acoustic unit are spaced apart from each other, these pressure differences do not occur, and a decrease in strength of the acoustic unit can be suppressed.

  In the acoustic damper of the present invention, the end portions of the acoustic units are arranged adjacent to each other.

  According to this acoustic damper, since the pressure difference in the portion where the pressure is relatively high in the mutual acoustic part can be reduced, it is possible to suppress the strength reduction of the terminal part of the mutual acoustic part.

  The acoustic damper according to the present invention is characterized in that the lengths from the entrance to the end of each of the acoustic parts are aligned.

  According to this acoustic damper, since the pressures at the end portions of the mutual acoustic portions are equal, the pressure difference between the mutual acoustic portions can be further reduced, and the strength reduction at the end portions of the mutual acoustic portions can be further suppressed. .

  Further, in the acoustic damper of the present invention, the acoustic unit forming a series of the passages is single, and the passages are arranged in a spiral shape adjacent to the periphery of the end portion of the passage of the acoustic unit. And the entrance and the end of the series of the passages are spaced apart.

  According to this acoustic damper, since the end portion having a high pressure in the passage of the acoustic portion is disposed between the passages, the pressure difference between the end portion and the surroundings is reduced, and the stress on the end portion is reduced. As a result, it is possible to suppress a decrease in strength of the terminal portion. In addition, since the entrance and the end of the passage of the acoustic unit are spaced apart from each other, these pressure differences do not occur, and a decrease in strength of the acoustic unit can be suppressed.

  Further, the acoustic damper of the present invention includes a plurality of the acoustic parts forming the series of the passages, and is adjacent to the periphery of the end portion of the passage of each of the acoustic parts. The passages of the acoustic parts are arranged so as to be spirally wound, and the entrance and the end of the passages of the acoustic parts are arranged apart from each other.

  According to this acoustic damper, since the terminal portion having a large pressure in the passage of each acoustic part is disposed between the passages of the other acoustic parts, the pressure difference from the surroundings becomes small in the terminal part, and the terminal part has Such stress is reduced. As a result, it is possible to suppress a decrease in strength of the terminal portion. In addition, since the entrance and end of the passage of each acoustic part are spaced apart from each other, these pressure differences do not occur, and a reduction in strength of the acoustic part can be suppressed.

  In order to achieve the above-described object, the combustor according to the present invention includes any one of the above-described acoustic dampers provided in the combustion cylinder, and causes air vibrations of the combustion gas flowing through the combustion cylinder to flow into the acoustic damper. It is characterized by.

  According to this combustor, pressure fluctuation in the combustor due to combustion vibration is attenuated by the acoustic unit.

  Further, in the combustor of the present invention, the longitudinal direction of the passage of the acoustic part is arranged along the circumferential direction of the combustion cylinder, and around the end part of the passage of the acoustic part in the axial direction of the combustion cylinder. A plurality of the passages are arranged adjacent to each other.

  According to this combustor, it is possible to prevent the occurrence of vibration that is displaced in the circumferential direction of the combustion cylinder. And since an acoustic part is provided along the outer surface of a combustion cylinder, combustor itself can be comprised comparatively small.

  Further, in the combustor of the present invention, the longitudinal direction of the passage of the acoustic part is arranged along the axial direction of the combustion cylinder, and around the end part of the passage of the acoustic part in the circumferential direction of the combustion cylinder. A plurality of the passages are arranged adjacent to each other.

  According to this combustor, it is possible to prevent the occurrence of vibration that is displaced in the axial direction of the combustion cylinder. And since an acoustic part is provided along the outer surface of a combustion cylinder, combustor itself can be comprised comparatively small.

  In order to achieve the above object, a gas turbine according to the present invention includes any one of the combustors described above.

  According to this gas turbine, the combustion vibration generated in the combustor is attenuated by the acoustic unit. As a result, noise and vibration during gas turbine operation can be reduced.

  ADVANTAGE OF THE INVENTION According to this invention, the strength fall of the channel | path which makes an acoustic part can be suppressed.

FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment of the present invention. FIG. 2 is a side view of the combustor according to the embodiment of the present invention. FIG. 3 is a side view of another example of the combustor according to the embodiment of the present invention. FIG. 4 is a configuration diagram of the acoustic damper according to the first embodiment of the present invention. FIG. 5 is a configuration diagram of another example of the acoustic damper according to the first embodiment of the present invention. FIG. 6 is a configuration diagram of another example of the acoustic damper according to the first embodiment of the present invention. FIG. 7 is a configuration diagram of an acoustic damper according to Embodiment 2 of the present invention. FIG. 8 is a configuration diagram of a conventional example for the acoustic damper according to the second embodiment of the present invention. FIG. 9 is a configuration diagram of an example for the acoustic damper according to the second embodiment of the present invention. FIG. 10 is a diagram illustrating a test result of the acoustic damper according to the second embodiment of the present invention. FIG. 11 is a configuration diagram of an acoustic damper according to Embodiment 3 of the present invention.

  Embodiments according to the present invention will be described below in detail with reference to the drawings. In addition, this invention is not limited by this embodiment. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same.

  FIG. 1 is a schematic configuration diagram of a gas turbine according to the present embodiment.

  As shown in FIG. 1, the gas turbine includes a compressor 11, a combustor 12, a turbine 13, and an exhaust chamber 14, and a generator (not shown) is connected to the compressor 11. The compressor 11 has an air intake 15 for taking in air, and a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner. In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20. The exhaust chamber 14 has an exhaust diffuser 23 that is continuous with the turbine 13. Further, the rotor 24 is positioned so as to pass through the central portion of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14, and the end portion on the compressor 11 side is rotatably supported by the bearing portion 25. On the other hand, the end portion on the exhaust chamber 14 side is rotatably supported by the bearing portion 26. A plurality of disk plates are fixed to the rotor 24, the rotor blades 18 and 22 are connected, and a drive shaft of a generator (not shown) is connected to an end portion on the compressor 11 side.

  Therefore, the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature and high-pressure compressed air. Combustion occurs when a predetermined fuel is supplied to the compressed air. The high-temperature and high-pressure combustion gas that is the working fluid generated in the combustor 12 passes through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. While the generator connected to 24 is driven, the exhaust gas is converted into static pressure by the exhaust diffuser 23 in the exhaust chamber 14 and then released to the atmosphere.

  2 and 3 are side views of the combustor according to the present embodiment.

  As shown in FIGS. 2 and 3, the combustor 12 has an inner cylinder 32 supported inside the casing housing 30 and the outer cylinder 31, and a tail cylinder 33 as a combustion cylinder is connected to the tip of the inner cylinder 32. ing.

  The outer cylinder 31 is fastened to the vehicle compartment housing 30. The inner cylinder 32 is provided in the outer cylinder 31 at a distance from the outer cylinder 31, and a pilot nozzle 35 is disposed along the axial direction that is the central portion of the inner cylinder 32 and that extends in the combustor shaft CE. Has been. The inner cylinder 32 has a plurality of main nozzles 36 arranged in parallel to the combustor axis CE so as to surround the pilot nozzles 35 along the circumferential direction on the inner peripheral surface of the inner cylinder 32. The tail tube 33 is formed in a cylindrical shape at the base end and connected to the tip of the inner tube 32. The tail tube 33 is curved and deformed with a cross-sectional area becoming smaller toward the tip side, and the tip is formed in a substantially rectangular shape. 13 is opened toward the first stage stationary vane 21 and is fastened to the vehicle compartment housing 30 via a gusset 37. The inner side of the tail cylinder 33 is configured as a combustion chamber. Note that the inside of the casing housing 30 is formed as a casing 38, and the tail cylinder 33 is provided in the casing 38.

  In such a combustor 12, the high-temperature and high-pressure compressed air from the compressor 11 flows into the inner cylinder 32 from the base end side of the inner cylinder 32 through the casing 38. This compressed air is guided to the pilot nozzle 35 and the main nozzle 36. The compressed air is mixed with the fuel injected from the main nozzle 36 and flows into the tail cylinder 33 as a premixed gas. The compressed air is mixed with fuel injected from the pilot nozzle 35, ignited by a not-shown type fire and burned, and is burned into the tail cylinder 33 as combustion gas. At this time, a part of the combustion gas is ejected so as to diffuse into the tail cylinder 33 with a flame, so that the premixed gas flowing into the tail cylinder 33 from each main nozzle 36 is ignited and burned. . That is, the flame holding for stable combustion of the lean premixed fuel from the main nozzle 36 can be performed by the diffusion flame by the pilot fuel injected from the pilot nozzle 35. Further, by premixing the fuel by the main nozzle 36, the fuel concentration can be made uniform, thereby reducing NOx. The combustion gas is supplied to the turbine 13 through the tail cylinder 33.

  By the way, as above-mentioned, it is called the axial direction which is the extension direction of the combustor axis | shaft CE. A direction around the outer cylinder 31, the inner cylinder 32, and the tail cylinder 33 around the combustor axis CE is referred to as a circumferential direction. Further, the extending direction (passing direction) of the radii of the outer cylinder 31, the inner cylinder 32, and the tail cylinder 33 in the direction perpendicular to the combustor axis CE is referred to as a radial direction.

[Embodiment 1]
4 to 6 are configuration diagrams of the acoustic damper according to the present embodiment.

  The above-described gas turbine combustor 12 generates vibration (combustion vibration) when the fuel is combusted. This combustion vibration causes noise and vibration during operation of the gas turbine. Therefore, as shown in FIGS. 2 and 3, the acoustic damper 1 is provided for the combustor 12 (tail tube 33) as a vibration generating source through which the combustion gas flows.

  As shown in FIGS. 2 and 3, the acoustic damper 1 is provided on the outer surface of the base end side of the tail cylinder 33 in the combustor 12. The acoustic damper 1 has a housing 2 that covers the outer side of the tail cylinder 33 as a vibration generation source. The housing 2 is formed in a box shape, the outer side of the tail tube 33 is opened, the opened periphery is bonded to the outer surface of the tail tube 33, and the inside is sealed with the outer surface of the tail tube 33.

  As shown in FIGS. 4 to 6, the acoustic damper 1 is formed with a passage 3 that forms an acoustic part N inside the housing 2. The passage 3 is formed in a series, and one end is configured as an inlet 3A that takes in air vibration generated by a vibration generation source. The inlet 3 </ b> A is provided to open toward the outer surface of the tail cylinder 33. The tail tube 33 is formed with a through hole (not shown) composed of a plurality of small holes through which air vibration (pressure wave) caused by internal combustion vibration passes outside at a position where the inlet 3A faces. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. Further, the passage 3 is configured as a terminal end 3B whose other end closes the downstream side of the propagation of the air vibration and becomes a resistance of the air vibration.

  In the acoustic damper 1, when fuel gas flows in the tail cylinder 33, air vibration (pressure wave) due to combustion vibration of this combustion gas passes through the through hole of the tail cylinder 33 and is taken into the passage 3 of the acoustic part N. It is. In the passage 3, the air vibration propagated between the inlet 3 </ b> A and the terminal end 3 </ b> B resonates, and the pressure fluctuation in the combustor 12 is attenuated.

  In the embodiment shown in FIGS. 4 to 6, the acoustic damper 1 includes a plurality of passages 3 of the acoustic part N extending in the longitudinal direction (passage longitudinal direction) L and in the short direction (passage width direction) S in the middle. It is formed so as to meander and fold into a step (three steps in FIGS. 4 to 6) P. The acoustic damper 1 has a plurality (two in FIGS. 4 to 6) of passages 3 of the acoustic part N. In the acoustic damper 1, the inlet 3 </ b> A and the terminal end 3 </ b> B of the series of passages 3 are spaced apart in each acoustic part N.

  The acoustic damper 1 shown in FIGS. 4 and 5 has an arrangement in which the passages 3 of the two acoustic parts N are reversed in the short direction S, and the ends 3B of the respective passages 3 are aligned in the longitudinal direction L. A terminal step P that is provided and extends along the longitudinal direction L including the terminal end 3 </ b> B is provided adjacently in the lateral direction S. That is, the passage 3 of each acoustic part N includes the terminal 3B and extends along the longitudinal direction L so as to be adjacent to the periphery of the stage P of the acoustic part N and other acoustics. A stage P of the passage 3 of the part N is arranged.

  The acoustic damper 1 shown in FIG. 6 is arranged such that the passages 3 of the two acoustic parts N are reversed with respect to each other in the short direction S, and the directions of the terminal ends 3B of the respective passages 3 are reversed with respect to the longitudinal direction L. In addition, a terminal step P including the terminal end 3B and extending along the longitudinal direction L is provided adjacently in the short direction S. That is, the passage 3 of each acoustic part N includes the terminal 3B and extends along the longitudinal direction L so as to be adjacent to the periphery of the stage P of the acoustic part N and other acoustics. A stage P of the passage 3 of the part N is arranged.

  According to the acoustic damper 1 of this embodiment, the stage P at the terminal end where the pressure is high in the path 3 of each acoustic part N is the stage P of the path 3 of the own acoustic part N and the path of other acoustic parts N. Since the third stage P is disposed between the three stages P, the pressure difference with the surroundings becomes small in the terminal stage P, and the stress applied to the terminal stage P decreases. As a result, it is possible to suppress a decrease in the strength of the stage P at the end portion. Moreover, according to the acoustic damper 1 of the present embodiment, the inlet 3A and the terminal end 3B of the passage 3 of the own acoustic unit N are spaced apart from each other, so that these pressure differences do not occur, and the own acoustic unit A decrease in the strength of N can be suppressed.

  In the acoustic damper 1 shown in FIG. 6, the end 3B of the passage 3 is provided adjacent to the inlet 3A of the passage 3 of the other acoustic unit N, but only a part of the end 3B of the other acoustic unit N is provided. Only adjacent to the entrance 3A of the passage 3 is a stage 3 of the passage 3 of the own acoustic part N and a stage P of the passage 3 of the other acoustic part N adjacent to the periphery of the stage P of the terminal part. Therefore, the strength reduction of the acoustic part N can be suppressed. 4 and 5, the acoustic damper 1 has its own acoustic part N without any pressure difference between the end 3B of the passage 3 and the inlet 3A of the passage 3 of the other acoustic part N. Strength reduction can be suppressed.

  Moreover, as shown in FIGS. 4-6, each acoustic part N is formed in the same step P, and since the termination | terminus parts of each channel | path 3 are arrange | positioning adjacent, pressure is mutually acoustic part N. Since the pressure difference at the relatively high portion can be reduced, it is possible to suppress a decrease in the strength of the stage P at the end portion of the mutual acoustic portion N.

  Moreover, as shown in FIG. 4 and FIG. 5, the terminal 3 </ b> B of each passage 3 of each acoustic part N is arranged adjacent to each other, so that the pressure difference at the highest pressure part in the mutual acoustic part N can be obtained. Since it can be made smaller, it is possible to further suppress a decrease in the strength of the stage P at the end portion of the mutual acoustic part N.

  Further, as shown in FIGS. 4 and 5, the pressures of the end portions of the acoustic parts N are equalized by aligning the lengths of the passages 3 of the acoustic parts N, so that the pressures of the mutual acoustic parts N are equal. A difference can be made smaller and the strength reduction of the stage P of the terminal part of the mutual acoustic part N can be suppressed more.

  Further, the combustor 12 of the present embodiment is provided with the acoustic damper 1 of any one of the forms described above in the tail cylinder (combustion cylinder) 33, and the vibration of the combustion gas flowing through the tail cylinder 33 is supplied to the acoustic damper 1. Let it flow.

  According to this combustor 12, pressure fluctuations in the combustor 12 due to combustion vibrations are attenuated by the acoustic part N.

  4 to 6, the longitudinal direction L is arranged along the circumferential direction of the combustor 12, and the short side direction S is arranged along the axial direction of the combustor 12. If comprised in this way, as shown in FIG. 2, the acoustic damper 1 will be arrange | positioned along the circumferential direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the circumferential direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  4 to 6, the longitudinal direction L is arranged along the axial direction of the combustor 12, and the short direction S is arranged along the circumferential direction of the combustor 12. If comprised in this way, as shown in FIG. 3, the acoustic damper 1 will be arrange | positioned along the axial direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the axial direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  4 to 6, the longitudinal direction L may be disposed along the circumferential direction of the combustor 12, and the short side direction S may be disposed along the radial direction of the combustor 12. . 4 to 6, the longitudinal direction L may be arranged along the axial direction of the combustor 12, and the short side direction S may be arranged along the radial direction of the combustor 12. . When the short direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A side of the passage 3 is opened to the outer surface of the tail tube 33 so that the inlet 3 </ b> A of the passage 3 opens toward the outer surface of the tail tube 33. Adjust to extend to the outside.

  Further, according to the gas turbine including the combustor 12 of the present embodiment, the combustion vibration generated in the combustor 12 by the acoustic unit N is attenuated. For this reason, the noise and vibration at the time of gas turbine operation can be reduced.

[Embodiment 2]
FIG. 7 is a configuration diagram of the acoustic damper according to the present embodiment.

  As shown in FIGS. 2 and 3, the acoustic damper 1 is provided on the outer surface of the base end side of the tail cylinder 33 in the combustor 12. The acoustic damper 1 has a housing 2 that covers the outer side of the tail cylinder 33 as a vibration generation source. The housing 2 is formed in a box shape, the outer side of the tail tube 33 is opened, the opened periphery is bonded to the outer surface of the tail tube 33, and the inside is sealed with the outer surface of the tail tube 33.

  As shown in FIG. 7, the acoustic damper 1 is formed with a passage 3 constituting an acoustic part N inside the housing 2. The passage 3 is formed in a series, and one end is configured as an inlet 3A that takes in air vibration generated by a vibration generation source. The inlet 3 </ b> A is provided to open toward the outer surface of the tail cylinder 33. The tail tube 33 is formed with a through hole (not shown) composed of a plurality of small holes through which air vibration (pressure wave) caused by internal combustion vibration passes outside at a position where the inlet 3A faces. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. Further, the passage 3 is configured as a terminal end 3B whose other end closes the downstream side of the propagation of the air vibration and becomes a resistance of the air vibration.

  In the acoustic damper 1, when fuel gas flows in the tail cylinder 33, air vibration (pressure wave) due to combustion vibration of this combustion gas passes through the through hole of the tail cylinder 33 and is taken into the passage 3 of the acoustic part N. It is. In the passage 3, the air vibration propagated between the inlet 3 </ b> A and the terminal end 3 </ b> B resonates, and the pressure fluctuation in the combustor 12 is attenuated.

  In the acoustic damper 1 shown in FIG. 7, the passage 3 of the acoustic portion N extends in the longitudinal direction (passage longitudinal direction) L, and has a plurality of stages (five stages in FIG. 7) in the lateral direction (passage width direction) S. ) It is formed by winding around P. Accordingly, in the acoustic damper 1, the passage 3 is arranged in a spiral shape so as to be adjacent to the periphery of the end portion having the end 3 </ b> B of the passage 3 of the acoustic portion N. In the acoustic damper 1, the inlet 3 </ b> A and the terminal end 3 </ b> B of the series of passages 3 of the acoustic unit N are arranged apart from each other.

  According to the acoustic damper 1 of the present embodiment as described above, since the end stage P having a large pressure in the passage 3 of the acoustic part N is disposed between the stage P of the passage 3, the end stage P , The pressure difference with the surroundings becomes small, and the stress related to the step P at the end portion decreases. As a result, it is possible to suppress a decrease in the strength of the stage P at the end portion. Moreover, according to the acoustic damper 1 of the present embodiment, the inlet 3A and the terminal end 3B of the passage 3 of the own acoustic unit N are spaced apart from each other, so that these pressure differences do not occur, and the own acoustic unit A decrease in the strength of N can be suppressed.

  Here, FIG. 8 is a configuration diagram of a conventional example for the acoustic damper according to the present embodiment. FIG. 9 is a configuration diagram of an example for the acoustic damper according to the present embodiment. FIG. 10 is a diagram illustrating a test result of the acoustic damper according to the present embodiment.

  In the acoustic damper 101 of the conventional example shown in FIG. 8, the passage 103 of the acoustic part M extends in the longitudinal direction (passage longitudinal direction) L, and has a plurality of stages in the short direction (passage width direction) S along the way (FIG. 8). In this case, the end portion having the end 103B of the passage 103 of the acoustic part M is disposed adjacent to one passage. In the acoustic damper 101 of this conventional example, the A surface, E surface, F surface, G surface, H surface, and I surface appear on the outside of the passage 103 from the inlet 103A to the terminal end 103B, and the B surface, C surface, and D surface. Are arranged between the passages 3. And the termination | terminus part of the acoustic part M appears on the table | surface by E surface, and the termination | terminus 103B has appeared on the table | surface by I surface.

  On the other hand, in the acoustic damper 1 of the embodiment shown in FIG. 9, the passage 3 of the acoustic part N extends in the longitudinal direction (passage longitudinal direction) L, and a plurality of stages in the short direction (passage width direction) S along the way ( In FIG. 9, the passage 3 is arranged so as to be adjacent to the periphery of the end portion having the end 3B of the passage 3 of the acoustic portion N. In the acoustic damper 1 of this embodiment, the A surface, the E surface, the F surface, and the G surface appear on the outside of the passage 3 from the inlet 3A to the terminal end 3B, and the B surface, the C surface, the D surface, the H surface, and the I surface. Are arranged between the passages 3. And the termination | terminus part of the acoustic part N is pinched | interposed into the channel | path 3 by D surface and H surface, and the termination | terminus 3B is adjacent to the channel | path 3 by I surface.

  When comparing the acoustic damper 101 of the conventional example and the acoustic damper 1 of the example, as shown in FIG. 10, the pressure [kPa] generated on each surface is determined by the end portion of the acoustic unit M in the acoustic damper 101 of the conventional example. The E surface that appears in the table has a markedly large peak, and it can be seen that the peak is suppressed as a whole in the acoustic damper 1 of the example.

  Further, the combustor 12 of the present embodiment is provided with the acoustic damper 1 of the above-described form in the tail cylinder (combustion cylinder) 33, and causes the air vibration of the combustion gas flowing through the tail cylinder 33 to flow into the acoustic damper 1.

  According to this combustor 12, pressure fluctuations in the combustor 12 due to combustion vibrations are attenuated by the acoustic part N.

  In the acoustic damper 1 shown in FIG. 7, the longitudinal direction L is disposed along the circumferential direction of the combustor 12, and the short direction S is disposed along the axial direction of the combustor 12. If comprised in this way, as shown in FIG. 2, the acoustic damper 1 will be arrange | positioned along the circumferential direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the circumferential direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  In the acoustic damper 1 shown in FIG. 7, the longitudinal direction L is disposed along the axial direction of the combustor 12, and the short direction S is disposed along the circumferential direction of the combustor 12. If comprised in this way, as shown in FIG. 3, the acoustic damper 1 will be arrange | positioned along the axial direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the axial direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  In the acoustic damper 1 shown in FIG. 7, the longitudinal direction L may be disposed along the circumferential direction of the combustor 12, and the short direction S may be disposed along the radial direction of the combustor 12. Further, the acoustic damper 1 shown in FIG. 7 may be arranged such that the longitudinal direction L is arranged along the axial direction of the combustor 12 and the short direction S is arranged along the radial direction of the combustor 12. When the short direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A side of the passage 3 is opened to the outer surface of the tail tube 33 so that the inlet 3 </ b> A of the passage 3 opens toward the outer surface of the tail tube 33. Adjust to extend to the outside.

  Further, according to the gas turbine including the combustor 12 of the present embodiment, the combustion vibration generated in the combustor 12 by the acoustic unit N is attenuated. For this reason, the noise and vibration at the time of gas turbine operation can be reduced.

[Embodiment 3]
FIG. 11 is a configuration diagram of the acoustic damper according to the present embodiment.

  As shown in FIGS. 2 and 3, the acoustic damper 1 is provided on the outer surface of the base end side of the tail cylinder 33 in the combustor 12. The acoustic damper 1 has a housing 2 that covers the outer side of the tail cylinder 33 as a vibration generation source. The housing 2 is formed in a box shape, the outer side of the tail tube 33 is opened, the opened periphery is bonded to the outer surface of the tail tube 33, and the inside is sealed with the outer surface of the tail tube 33.

  As shown in FIG. 11, the acoustic damper 1 is formed with a passage 3 constituting an acoustic part N inside the housing 2. The passage 3 is formed in a series, and one end is configured as an inlet 3A that takes in air vibration generated by a vibration generation source. The inlet 3 </ b> A is provided to open toward the outer surface of the tail cylinder 33. The tail tube 33 is formed with a through hole (not shown) composed of a plurality of small holes through which air vibration (pressure wave) caused by internal combustion vibration passes outside at a position where the inlet 3A faces. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. Further, the passage 3 is configured as a terminal end 3B whose other end closes the downstream side of the propagation of the air vibration and becomes a resistance of the air vibration.

  In the acoustic damper 1, when fuel gas flows in the tail cylinder 33, air vibration (pressure wave) due to combustion vibration of this combustion gas passes through the through hole of the tail cylinder 33 and is taken into the passage 3 of the acoustic part N. It is. In the passage 3, the air vibration propagated between the inlet 3 </ b> A and the terminal end 3 </ b> B resonates, and the pressure fluctuation in the combustor 12 is attenuated.

  In the acoustic damper 1 shown in FIG. 11, the passage 3 of the acoustic part N extends in the longitudinal direction (passage longitudinal direction) L, and has a plurality of stages (three stages in FIG. 11) in the lateral direction (passage width direction) S. ). Accordingly, in the acoustic damper 1, the passage 3 is arranged in a spiral shape so as to be adjacent to the periphery of the end portion having the end 3 </ b> B of the passage 3 of the acoustic portion N. In the acoustic damper 1, the inlet 3 </ b> A and the terminal end 3 </ b> B of the series of passages 3 of the acoustic unit N are arranged apart from each other. The acoustic damper 1 shown in FIG. 11 has a plurality (two) of passages 3 for the acoustic part N. The passages 3 of each acoustic part N are provided with the spirals wound in opposite directions, with the ends 3B of the respective passages 3 reversed in the longitudinal direction L and including the terminations 3B in the longitudinal direction L. Steps P1 and P2 of the end portion extending along the short side direction S are provided adjacent to each other. That is, the path 3 of each acoustic part N is adjacent to the periphery of the stage P1 (or P2) of the terminal part including the terminal 3B and extends along the longitudinal direction L, and the stage P2 of the path 3 of the other acoustic part N. (Or P1).

  According to the acoustic damper 1 of this embodiment, the stage P1 (or P2) at the terminal end where the pressure is high in the passage 3 of each acoustic part N is the stage P2 (or P1) of the path 3 of the other acoustic part N. Therefore, the pressure difference with respect to the surroundings is reduced in the terminal step P1 (or P2), and the stress related to the terminal step P1 (or P2) is reduced. As a result, it is possible to suppress a decrease in strength of the terminal stage P1 (or P2). Moreover, according to the acoustic damper 1 of the present embodiment, since the inlet 3A and the terminal end 3B of the passage 3 of each acoustic part N are arranged apart from each other, these pressure differences do not occur, and the strength of the acoustic part N The decrease can be suppressed.

  Further, the combustor 12 of the present embodiment is provided with the acoustic damper 1 of the above-described form in the tail cylinder (combustion cylinder) 33, and causes the air vibration of the combustion gas flowing through the tail cylinder 33 to flow into the acoustic damper 1.

  According to this combustor 12, pressure fluctuations in the combustor 12 due to combustion vibrations are attenuated by the acoustic part N.

  In the acoustic damper 1 shown in FIG. 11, the longitudinal direction L is disposed along the circumferential direction of the combustor 12, and the short direction S is disposed along the axial direction of the combustor 12. If comprised in this way, as shown in FIG. 2, the acoustic damper 1 will be arrange | positioned along the circumferential direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the circumferential direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  In the acoustic damper 1 shown in FIG. 11, the longitudinal direction L is disposed along the axial direction of the combustor 12, and the short direction S is disposed along the circumferential direction of the combustor 12. If comprised in this way, as shown in FIG. 3, the acoustic damper 1 will be arrange | positioned along the axial direction mainly on the outer surface of the transition piece 33. FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that is displaced in the axial direction of the transition piece 33. And since the acoustic part N is provided along the outer surface of the tail cylinder 33, combustor 12 itself can be comprised comparatively small.

  Note that the acoustic damper 1 shown in FIG. 11 may be disposed such that the longitudinal direction L is along the circumferential direction of the combustor 12 and the short direction S is disposed along the radial direction of the combustor 12. Further, the acoustic damper 1 shown in FIG. 11 may be arranged such that the longitudinal direction L is arranged along the axial direction of the combustor 12 and the short direction S is arranged along the radial direction of the combustor 12. When the short direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A side of the passage 3 is opened to the outer surface of the tail tube 33 so that the inlet 3 </ b> A of the passage 3 opens toward the outer surface of the tail tube 33. Adjust to extend to the outside.

  Further, according to the gas turbine including the combustor 12 of the present embodiment, the combustion vibration generated in the combustor 12 by the acoustic unit N is attenuated. As a result, noise and vibration during gas turbine operation can be reduced.

DESCRIPTION OF SYMBOLS 1 Acoustic damper 2 Housing 3 Passage 3A Inlet 3B Terminal N Acoustic part P, P1, P2 Stage L Longitudinal direction S Short direction 11 Compressor 12 Combustor 13 Turbine 14 Exhaust chamber 15 Air intake 16 Compressor casing 17 Stator blade 18 Rotor blade 20 Turbine casing 21 Stator blade 22 Rotor blade 23 Exhaust diffuser 24 Rotor 25 Bearing portion 26 Bearing portion 30 Casing housing 31 Outer cylinder 32 Inner cylinder 33 Tail cylinder 35 Pilot nozzle 36 Main nozzle 37 Gusset 38 Chamber CE Combustor Axis 101 Conventional acoustic damper 103 Passage 103A Inlet 103B Termination M Sound part

Claims (10)

An acoustic damper fixed to the vibration source and provided along the outer surface of the vibration source,
An acoustic part that forms a series of passages having an inlet for taking in air vibrations generated by the vibration source and a terminal end that becomes a resistance to the air vibrations by closing a downstream side of propagation of the air vibrations;
The acoustic unit is characterized in that the passage is folded and a plurality of the passages are arranged adjacent to each other around a terminal portion, and the entrance and the terminal of the series of the passages are spaced apart from each other. An acoustic damper.   A plurality of the acoustic parts forming a series of the passages are provided, and the passages of the acoustic parts of the acoustic parts and the passages of the other acoustic parts are arranged adjacent to the periphery of the end portions of the passages of the acoustic parts. 2. The acoustic damper according to claim 1, wherein the entrance and the terminal end of the passage of each of the acoustic units are spaced apart from each other.   The acoustic damper according to claim 2, wherein terminal portions of the acoustic units are arranged adjacent to each other.   The acoustic damper according to claim 3, wherein the lengths of the ends from the entrance of each of the acoustic parts are aligned.   A single acoustic part forming a series of the passages, the passages being spirally disposed adjacent to the periphery of the end of the passage of the acoustic part, and the acoustic parts of the series of the passages; The acoustic damper according to claim 1, wherein the inlet and the terminal end are spaced apart from each other.   A plurality of the acoustic parts forming a series of the passages are provided, and the passages of the acoustic parts and the other acoustic parts are spirally adjacent to the periphery of the end portions of the passages of the acoustic parts. 2. The acoustic damper according to claim 1, wherein the acoustic damper is disposed so as to be wound around, and the entrance and the end of the passage of each of the acoustic units are spaced apart from each other.   A combustor, wherein the acoustic damper according to any one of claims 1 to 6 is provided in a combustion cylinder, and air vibrations of combustion gas flowing through the combustion cylinder are caused to flow into the acoustic damper.   The longitudinal direction of the passage of the acoustic part is arranged along the circumferential direction of the combustion cylinder, and the plurality of passages are arranged adjacent to the periphery of the end part of the passage of the acoustic part in the axial direction of the combustion cylinder The combustor according to claim 7.   The longitudinal direction of the passage of the acoustic part is arranged along the axial direction of the combustion cylinder, and a plurality of the passages are arranged adjacent to the periphery of the end part of the passage of the acoustic part in the circumferential direction of the combustion cylinder The combustor according to claim 7.   A gas turbine comprising the combustor according to any one of claims 7 to 9.

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