JP6640581B2 - Acoustic dampers, combustors and gas turbines - Google Patents

Description

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

  Conventionally, for example, in Patent Literature 1, in order to improve damping performance and maintainability, an acoustic liner having an acoustic liner resonance space including a perforated plate and a housing, and an acoustic liner resonance space connected to the housing and inside. And an acoustic damper having an acoustic damper resonance space communicating with the damper. In this damping device, an acoustic liner is mounted around a transition piece of a combustor, and an acoustic damper is provided along an extending direction of the transition piece.

  Conventionally, for example, in Patent Literature 2, in order to reduce the mounting space of the acoustic damper and reduce the size, and to improve the maintainability, the acoustic section having the acoustic damper resonance space of the acoustic damper has a combustion area inside. It is folded at least once along the cylindrical body to be formed.

  Conventionally, for example, in Patent Literature 3, in order to reduce vibration in a wide frequency band, an acoustic damper having a passage (pipe) having an opening and including a resistor for giving resistance to a fluid flowing through the passage is provided. Is disclosed. In this acoustic damper, a passage and a resistor that are bent 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. Are communicated through.

JP-A-2006-26671 Japanese Patent No. 5291790 JP 2006-22966 A

  In each of the above-mentioned Patent Documents 1, 2, and 3, the acoustic portion is such that one end of a passage forming an acoustic liner resonance space serves as an inlet for taking in air vibration from a vibration source such as a combustion tube, and the other end is terminated. Thus, it is a resonance box, and in the passage, a pressure fluctuation occurs in which the pressure gradually increases from the entrance to the end.

  In such a configuration, in Patent Literature 1 and Patent Literature 2, each side of the end portion of the passage, which is the acoustic portion, appears in the table so as to be in contact with non-vibrated air. The pressure fluctuation of the non-vibrating air is almost 0 kPa. On the other hand, when air vibration is taken in from the vibration source and the pressure fluctuation at the terminal resonating in the acoustic tube is set to, for example, 100 kPa, each side of the terminal portion near 100 kPa Since it is closer to 0 kPa, a large stress may be applied due to the pressure difference, and the strength may be reduced.

  Further, in Patent Document 3, a first layer having a resonance box in which a circular tube is spirally wound and having an inlet for taking in air vibration from a vibration source and a second layer having an end form one passage. The first layer is formed spirally from the inside to the outside with the inlet at the center, and the second layer is formed spirally from the outside to the inside with the end at the center. I have. In such a configuration, the inlet and the terminal end are arranged adjacent to each other, and there is a possibility that a large stress is applied due to a difference between these pressures and the strength is reduced.

  An object of the present invention is to solve the above-mentioned problem, and an object of the present invention is to provide an acoustic damper, a combustor, and a gas turbine that can suppress a decrease in strength of a passage forming an acoustic part.

  In order to achieve the above object, an acoustic damper according to the present invention is an acoustic damper fixed to a vibration source and provided along an outer surface of the vibration source, the air damper being generated by the vibration source. And an end that becomes a resistance to the air vibration by closing the downstream side of the propagation of the air vibration, and includes a sound part forming a series of passages, wherein the sound part is formed by folding the passage. A plurality of the passages are arranged adjacent to a terminal portion, and the entrance and the terminal end of a 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 large in the passage of the acoustic portion is interposed between the passages, the pressure difference between the end portion and the periphery is reduced, and the stress on the end portion is reduced. I do. As a result, it is possible to suppress a decrease in the strength of the terminal portion. In addition, since the entrance and the end of the passage of the own acoustic section are arranged apart from each other, these pressure differences do not occur, and the decrease in the strength of the own acoustic section can be suppressed.

  Further, in the acoustic damper of the present invention, a plurality of the acoustic portions forming a series of the passages are provided. The passages of the sound unit are arranged, and the entrance and the end of the passage of each sound unit are spaced apart from each other.

  According to this acoustic damper, since the periphery of the end portion of the plurality of acoustic portions that has a large pressure is sandwiched between the own passage and the passage of the other acoustic portion, the acoustic damper is located between the end portion and the periphery. The pressure difference becomes smaller, and the stress applied to the terminal portion decreases. As a result, it is possible to suppress a decrease in the strength of the terminal portion. In addition, since the entrance and the end of the passage of the own acoustic section are arranged apart from each other, these pressure differences do not occur, and the decrease in the strength of the own acoustic section can be suppressed.

  Further, in the acoustic damper of the present invention, the terminal portions of the acoustic portions are arranged adjacent to each other.

  According to this acoustic damper, since the pressure difference between the relatively high pressure portions of the mutual acoustic portions can be reduced, the decrease in the strength of the terminal portions of the mutual acoustic portions can be suppressed.

  Further, the acoustic damper of the present invention is characterized in that the lengths from the entrance to the end of each of the acoustic sections are equalized.

  According to this acoustic damper, since the pressures at the end portions of the mutual acoustic portions become equal, the pressure difference between the mutual acoustic portions can be made smaller, and a decrease in the strength of the terminal portions of the mutual acoustic portions can be further suppressed. .

  Further, in the acoustic damper of the present invention, the acoustic portion forming the series of the passages has a single acoustic portion, and the passages are spirally disposed adjacent to the periphery of the terminal portion of the passage of the acoustic portion. And the inlet and the end of a series of the passages are spaced apart.

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

  Further, in the acoustic damper of the present invention, a plurality of the acoustic portions forming a series of the passages are provided. The passage of the acoustic section may be spirally arranged, and the entrance and the end of the passage of each acoustic section may be spaced apart.

  According to this acoustic damper, in the passage of each acoustic portion, the terminal portion having a large pressure is disposed so as to be sandwiched between the passages of other acoustic portions. Such stress decreases. As a result, it is possible to suppress a decrease in the strength of the terminal portion. In addition, since the entrance and the end of the passage of each acoustic portion are arranged apart from each other, these pressure differences do not occur, and a decrease in the strength of the acoustic portion can be suppressed.

  In order to achieve the above-mentioned object, a combustor of the present invention is provided with any one of the above-described acoustic dampers in a combustion cylinder, and allows air vibration of combustion gas flowing through the combustion cylinder to flow into the acoustic damper. It is characterized by.

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

  Further, in the combustor of the present invention, the longitudinal direction of the passage of the acoustic section is arranged along the circumferential direction of the combustion cylinder, and the periphery of the end section of the passage of the acoustic section 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 displaces in the circumferential direction of the combustion cylinder. Moreover, since the acoustic portion is provided along the outer surface of the combustion cylinder, the combustor itself can be configured to be relatively small.

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

  According to this combustor, it is possible to prevent the generation of vibration that displaces in the axial direction of the combustion cylinder. Moreover, since the acoustic portion is provided along the outer surface of the combustion cylinder, the combustor itself can be configured to be relatively small.

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

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

  ADVANTAGE OF THE INVENTION According to this invention, the fall of the intensity | strength of the path | pass which comprises 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 the acoustic damper according to the second embodiment of the present invention. FIG. 8 is a configuration diagram of a conventional example of an acoustic damper according to Embodiment 2 of the present invention. FIG. 9 is a configuration diagram of an example of the acoustic damper according to the second embodiment of the present invention. FIG. 10 is a diagram illustrating test results 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.

  Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. Note that the present invention is not limited by the embodiment. The components 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 capable of supplying fuel to the compressed air compressed by the compressor 11 and igniting with a burner so as to be combustible. 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 connected to the turbine 13. Further, the rotor 24 is positioned so as to pass through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14, and the end on the compressor 11 side is rotatably supported by the bearing 25. On the other hand, the end on the exhaust chamber 14 side is rotatably supported by a bearing 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 on the compressor 11 side.

  Therefore, the air taken in from the air inlet 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. The combustion is performed by supplying a predetermined fuel to the compressed air. Then, a high-temperature and high-pressure combustion gas, which is a working fluid generated in the combustor 12, passes through a plurality of stationary blades 21 and a moving blade 22 constituting the turbine 13 to drive and rotate a rotor 24. While driving the generator connected to 24, the exhaust gas is converted to static pressure by the exhaust diffuser 23 of 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 30 and the outer cylinder 31, and a tail pipe 33 as a combustion cylinder is connected to a distal end of the inner cylinder 32. ing.

  The outer cylinder 31 is fastened to the vehicle interior housing 30. The inner cylinder 32 is provided at a distance from the outer cylinder 31 in the outer cylinder 31, and a pilot nozzle 35 is disposed at a central portion inside the outer cylinder 31 along an axial direction which is an extending direction of the combustor axis CE. Have been. The inner cylinder 32 has a plurality of main nozzles 36 arranged in parallel with the combustor axis CE so as to surround the pilot nozzle 35 along the circumferential direction on the inner peripheral surface inside the inner cylinder 32. The tail tube 33 has a base end formed in a cylindrical shape and is connected to the front end of the inner tube 32. The tail tube 33 is curved and deformed with a reduced cross-sectional area toward the front end side. 13, and is open to the first stage stationary blade 21, and is fastened to the vehicle interior housing 30 via a gusset 37. The transition piece 33 has a combustion chamber on the inside. The interior of the vehicle housing 30 is formed as a vehicle interior 38, and the transition piece 33 is provided in the vehicle interior 38.

  In such a combustor 12, 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 via the vehicle interior 38. This compressed air is guided to a pilot nozzle 35 and a main nozzle 36. Then, the compressed air is mixed with the fuel injected from the main nozzle 36 and flows into the transition piece 33 as a premixed air. The compressed air is mixed with the fuel injected from the pilot nozzle 35, ignited by a pilot flame (not shown), burned, and emitted as combustion gas into the transition piece 33. At this time, a part of the combustion gas is jetted into the transition piece 33 so as to be diffused around with a flame, so that the premixed gas flowing into the transition piece 33 from each main nozzle 36 is ignited and burned. . That is, a flame holding for performing 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 to make the fuel concentration uniform, it is possible to reduce NOx. Then, the combustion gas is supplied to the turbine 13 through the transition piece 33.

  By the way, as described above, it is referred to as an axial direction which is an extending direction of the combustor axis CE. Further, a direction around the outer cylinder 31, the inner cylinder 32, and the transition piece 33 around the combustor axis CE is referred to as a circumferential direction. The direction perpendicular to the combustor axis CE and in which the outer cylinder 31, the inner cylinder 32, and the tail cylinder 33 extend (radially extending direction) 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 combustor 12 of the gas turbine generates vibration (combustion vibration) when fuel is burned. This combustion vibration causes noise and vibration during gas turbine operation. Therefore, as shown in FIGS. 2 and 3, the acoustic damper 1 is provided for the combustor 12 (tail tube 33) as a vibration 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 combustor 12 on the base end side of the transition piece 33. The acoustic damper 1 has a housing 2 that covers the outside of a transition piece 33 as a vibration source. The housing 2 is formed in a box shape, the outside of the transition piece 33 is opened, the opened rim is adhered to the outer surface of the transition piece 33, and the inside is sealed with the outer surface of the transition piece 33.

  As shown in FIGS. 4 to 6, the acoustic damper 1 has a passage 3 that forms an acoustic portion N inside a housing 2. The passage 3 is formed so as to be connected in series, and one end is configured as an inlet 3A for taking in air vibration generated by the vibration generation source. The inlet 3 </ b> A is provided so as to open toward the outer surface of the transition piece 33. In the transition piece 33, a through-hole (not shown) made up of a plurality of small holes is formed at a position facing the inlet 3A to allow air vibrations (pressure waves) due to the internal combustion vibration to pass outward. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. In addition, 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 serves as a resistance to the air vibration.

  When the fuel gas flows through the transition piece 33, the acoustic damper 1 captures air vibrations (pressure waves) due to the combustion vibration of the combustion gas through the through holes of the transition piece 33 and into the passage 3 of the acoustic portion N. It is. Then, in the passage 3, the air vibration propagated between the inlet 3A and the end 3B resonates, and the pressure fluctuation in the combustor 12 is attenuated.

  In the embodiment shown in FIGS. 4 to 6, the acoustic damper 1 is configured such that the passage 3 of the acoustic portion N extends in the longitudinal direction (pass longitudinal direction) L and has a plurality of passages in the transverse direction (pass width direction) S in the middle. It is folded back to a step (three steps in FIGS. 4 to 6) P and formed to meander. The acoustic damper 1 has a plurality of (two in FIGS. 4 to 6) passages 3 of the acoustic part N. The acoustic damper 1 is arranged such that the entrance 3A and the end 3B of the series of passages 3 are separated from each other in each acoustic portion N.

  The acoustic damper 1 shown in FIGS. 4 and 5 is configured such that the passages 3 of the two acoustic portions N are inverted from each other in the lateral direction S, and the ends 3B of the passages 3 are aligned in the longitudinal direction L. A step P of a terminal portion provided and extending along the longitudinal direction L including the terminal end 3B is provided adjacently in the short direction S. That is, the passage 3 of each sound portion N is adjacent to the step P of the terminal portion including the terminal end 3B and extending along the longitudinal direction L and adjacent to the step P of the passage 3 of the own sound portion N and the other sound. The step P of the passage 3 of the section N is arranged.

  The acoustic damper 1 shown in FIG. 6 has a configuration in which the passages 3 of the two acoustic portions N are reversed in the short direction S, and the ends 3B of the respective passages 3 are reversed in the longitudinal direction L. A step P of a terminal portion including the terminal end 3B and extending along the longitudinal direction L is provided adjacently in the lateral direction S. That is, the passage 3 of each sound portion N is adjacent to the step P of the terminal portion including the terminal end 3B and extending along the longitudinal direction L and adjacent to the step P of the passage 3 of the own sound portion N and the other sound. The step P of the passage 3 of the section N is arranged.

  According to such an acoustic damper 1 of the present embodiment, in the passage 3 of each acoustic section N, the step P at the terminal end where the pressure is large is the step P of the passage 3 of the own acoustic section N and the passage of the other acoustic section N. Since the third stage P is interposed between the third stage P, the pressure difference between the third stage P and the surroundings is small, and the stress related to the last stage P is reduced. As a result, a decrease in the strength of the step P at the terminal end can be suppressed. Moreover, according to the acoustic damper 1 of the present embodiment, since the entrance 3A and the end 3B of the passage 3 of the own acoustic part N are arranged apart from each other, these pressure differences do not occur, and the own acoustic part 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 entrance 3A of the passage 3 of the other acoustic portion N, but only a part of the end 3B of the other acoustic portion N is provided. Only adjacent to the entrance 3A of the passage 3, the stage P of the passage 3 of the own acoustic portion N and the stage P of the passage 3 of the other acoustic portion N are arranged adjacent to the periphery of the stage P at the terminal end. Therefore, it is possible to suppress a decrease in the strength of the acoustic portion N. 4 and 5, the end 3B of the passage 3 is separated from the entrance 3A of the passage 3 of the other acoustic part N, so that these pressure differences do not occur, and the acoustic damper 1 has its own acoustic part N. Can be suppressed from decreasing in strength.

  Further, as shown in FIGS. 4 to 6, each acoustic portion N is formed in the same step P, and the end portions of each passage 3 are arranged adjacent to each other, so that a pressure is generated in the mutual acoustic portions N. Since the pressure difference at a relatively high portion can be reduced, a decrease in the strength of the step P at the end of the mutual acoustic portion N can be suppressed.

  In addition, as shown in FIGS. 4 and 5, by arranging the end 3B of each passage 3 of each acoustic part N adjacent to each other, the pressure difference between the parts where the pressure is highest in the mutual acoustic parts N is reduced. Since the size can be made smaller, it is possible to further suppress a decrease in the strength of the step P at the end part of the mutual sound part N.

  Further, as shown in FIGS. 4 and 5, by equalizing the lengths of the passages 3 of the respective acoustic portions N, the pressures at the end portions of the respective acoustic portions N are equalized. The difference can be made smaller, and a decrease in the strength of the step P at the end of the mutual sound part N can be further suppressed.

  Further, the combustor 12 of the present embodiment is provided with the acoustic damper 1 of any one of the above-mentioned forms in the transition piece (combustion cylinder) 33, and applies the air vibration of the combustion gas flowing through the transition piece 33 to the acoustic damper 1. Let it flow in.

  According to the combustor 12, pressure fluctuation in the combustor 12 due to combustion vibration is attenuated by the acoustic part N.

  The acoustic damper 1 shown in FIGS. 4 to 6 has the longitudinal direction L arranged along the circumferential direction of the combustor 12 and the short direction S arranged along the axial direction of the combustor 12. With this configuration, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the circumferential direction, as shown in FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that displaces in the circumferential direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  4 to 6, the longitudinal direction L is arranged along the axial direction of the combustor 12, and the transverse direction S is arranged along the circumferential direction of the combustor 12. With such a configuration, as shown in FIG. 3, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the axial direction.

  According to the combustor 12, it is possible to prevent occurrence of vibration that displaces in the axial direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  In addition, the acoustic damper 1 shown in FIGS. 4 to 6 may be arranged such that the longitudinal direction L is arranged along the circumferential direction of the combustor 12 and the short direction S is arranged 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 direction S may be arranged along the radial direction of the combustor 12. . When the short side direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A of the passage 3 is connected to the transition piece 33 so that the entrance 3 </ b> A of the passage 3 opens toward the outer surface of the transition piece 33. Adjust to extend toward the outer surface.

  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 part N is attenuated. Therefore, noise and vibration during operation of the gas turbine 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 combustor 12 on the base end side of the transition piece 33. The acoustic damper 1 has a housing 2 that covers the outside of a transition piece 33 as a vibration source. The housing 2 is formed in a box shape, the outside of the transition piece 33 is opened, the opened rim is adhered to the outer surface of the transition piece 33, and the inside is sealed with the outer surface of the transition piece 33.

  As shown in FIG. 7, the acoustic damper 1 has a passage 3 that forms an acoustic part N inside a housing 2. The passage 3 is formed so as to be connected in series, and one end is configured as an inlet 3A for taking in air vibration generated by the vibration generation source. The inlet 3 </ b> A is provided so as to open toward the outer surface of the transition piece 33. In the transition piece 33, a through-hole (not shown) made up of a plurality of small holes is formed at a position facing the inlet 3A to allow air vibrations (pressure waves) due to the internal combustion vibration to pass outward. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. In addition, 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 serves as a resistance to the air vibration.

  When the fuel gas flows through the transition piece 33, the acoustic damper 1 captures air vibrations (pressure waves) due to the combustion vibration of the combustion gas through the through holes of the transition piece 33 and into the passage 3 of the acoustic portion N. It is. Then, in the passage 3, the air vibration propagated between the inlet 3A and the end 3B 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 part N extends in the longitudinal direction (longitudinal direction of the passage) L, and a plurality of stages (five in FIG. ) It is formed by winding around P. Thereby, in the acoustic damper 1, the passage 3 is spirally arranged so as to be adjacent to the periphery of the terminal portion 3B having the terminal end 3B of the passage 3 of the acoustic portion N. The acoustic damper 1 is arranged such that the entrance 3A of the series of passages 3 of the acoustic section N and the terminal end 3B are separated from each other.

  According to the acoustic damper 1 of the present embodiment as described above, since the step P of the terminal end where the pressure is large in the passage 3 of the acoustic part N is interposed between the steps P of the passage 3, the step P of the terminal end is arranged. , The pressure difference from the surroundings is reduced, and the stress on the step P at the terminal end is reduced. As a result, a decrease in the strength of the step P at the terminal end can be suppressed. Moreover, according to the acoustic damper 1 of the present embodiment, since the entrance 3A and the end 3B of the passage 3 of the own acoustic part N are arranged apart from each other, these pressure differences do not occur, and the own acoustic part A decrease in the strength of N can be suppressed.

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

  In the conventional acoustic damper 101 shown in FIG. 8, the passage 103 of the acoustic portion M extends in the longitudinal direction (longitudinal direction of the passage) L, and a plurality of steps in the short direction (passage width direction) S in the middle (FIG. 8). In the acoustic section M, the end portion having the end 103B of the passage 103 is disposed adjacent to only one passage. In the acoustic damper 101 of this conventional example, the A, E, F, G, H, and I surfaces appear outside the passage 103 from the entrance 103A to the terminal end 103B, and the B, C, and D surfaces Are arranged between the passages 3. Then, the terminal end of the acoustic part M appears on the surface E, and the terminal 103B appears on the surface I.

  On the other hand, in the acoustic damper 1 of the embodiment shown in FIG. 9, the passage 3 of the acoustic portion N extends in the longitudinal direction (longitudinal direction of the passage) L, and a plurality of steps (the widthwise direction of the passage) S in the middle. The passage 3 is arranged so as to be adjacent to the end of the acoustic portion N having the end 3B, which is formed in a spiral shape by being wound around P (four stages in FIG. 9). In the acoustic damper 1 of this embodiment, the surfaces A, E, F, and G appear outside the passage 3 from the entrance 3A to the end 3B, and the surfaces B, C, D, H, and I Are arranged between the passages 3. The end of the acoustic portion N is sandwiched between the passages 3 on the D and H surfaces, and the end 3B is adjacent to the passage 3 on the I surface.

  Comparing the conventional acoustic damper 101 with the acoustic damper 1 of the embodiment, as shown in FIG. 10, the pressure [kPa] generated on each surface is such that the end of the acoustic portion M in the conventional acoustic damper 101 is The E-plane appearing in the table has a remarkably large peak, and it can be seen that the peak is suppressed as a whole in the acoustic damper 1 of the embodiment.

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

  According to the combustor 12, pressure fluctuation in the combustor 12 due to combustion vibration is attenuated by the acoustic part N.

  Note that, in the acoustic damper 1 shown in FIG. 7, the longitudinal direction L is arranged along the circumferential direction of the combustor 12, and the lateral direction S is arranged along the axial direction of the combustor 12. With this configuration, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the circumferential direction, as shown in FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that displaces in the circumferential direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  In the acoustic damper 1 shown in FIG. 7, 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. With such a configuration, as shown in FIG. 3, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the axial direction.

  According to the combustor 12, it is possible to prevent occurrence of vibration that displaces in the axial direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  Note that, in the acoustic damper 1 shown in FIG. 7, the longitudinal direction L may be arranged along the circumferential direction of the combustor 12, and the short direction S may be arranged along the radial direction of the combustor 12. The acoustic damper 1 shown in FIG. 7 may have the longitudinal direction L arranged along the axial direction of the combustor 12 and the short direction S arranged along the radial direction of the combustor 12. When the short side direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A of the passage 3 is connected to the transition piece 33 so that the entrance 3 </ b> A of the passage 3 opens toward the outer surface of the transition piece 33. Adjust to extend toward the outer surface.

  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 part N is attenuated. Therefore, noise and vibration during operation of the gas turbine 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 combustor 12 on the base end side of the transition piece 33. The acoustic damper 1 has a housing 2 that covers the outside of a transition piece 33 as a vibration source. The housing 2 is formed in a box shape, the outside of the transition piece 33 is opened, the opened rim is adhered to the outer surface of the transition piece 33, and the inside is sealed with the outer surface of the transition piece 33.

  As shown in FIG. 11, the acoustic damper 1 has a passage 3 forming an acoustic portion N inside a housing 2. The passage 3 is formed so as to be connected in series, and one end is configured as an inlet 3A for taking in air vibration generated by the vibration generation source. The inlet 3 </ b> A is provided so as to open toward the outer surface of the transition piece 33. In the transition piece 33, a through-hole (not shown) made up of a plurality of small holes is formed at a position facing the inlet 3A to allow air vibrations (pressure waves) due to the internal combustion vibration to pass outward. Air vibration is taken into the passage 3 from the inlet 3A through the through hole. In addition, 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 serves as a resistance to the air vibration.

  When the fuel gas flows through the transition piece 33, the acoustic damper 1 captures air vibrations (pressure waves) due to the combustion vibration of the combustion gas through the through holes of the transition piece 33 and into the passage 3 of the acoustic portion N. It is. Then, in the passage 3, the air vibration propagated between the inlet 3A and the end 3B 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 portion N extends in the longitudinal direction (passage longitudinal direction) L, and a plurality of stages (3 stages in FIG. ). Thereby, in the acoustic damper 1, the passage 3 is spirally arranged so as to be adjacent to the periphery of the terminal portion 3B having the terminal end 3B of the passage 3 of the acoustic portion N. The acoustic damper 1 is arranged such that the entrance 3A of the series of passages 3 of the acoustic section N and the terminal end 3B are separated from each other. The acoustic damper 1 shown in FIG. 11 has a plurality of (two) passages 3 of the acoustic part N. The passages 3 of the respective acoustic portions N are provided such that the spirals are wound in opposite directions, and the ends 3B of the respective passages 3 are reversed in the longitudinal direction L. Steps P1 and P2 of the terminal end portion extending along are provided adjacently in the lateral direction S. That is, the passage 3 of each acoustic part N is adjacent to the periphery of the step P1 (or P2) of the terminal part including the terminal end 3B and extending along the longitudinal direction L, and the step P2 of the passage 3 of the other acoustic part N (Or P1).

  According to such an acoustic damper 1 of the present embodiment, the stage P1 (or P2) of the end portion where the pressure is large in the passage 3 of each acoustic portion N is changed to the stage P2 (or P1) of the passage 3 of the other acoustic portion N. , The pressure difference from the surroundings at the terminal step P1 (or P2) is reduced, and the stress applied to the terminal step P1 (or P2) is reduced. As a result, it is possible to suppress a decrease in the strength of the step P1 (or P2) at the terminal end. In addition, according to the acoustic damper 1 of the present embodiment, since the entrance 3A and the end 3B of the passage 3 of each acoustic section N are arranged apart from each other, no pressure difference occurs between them and the strength of the acoustic section 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 embodiment in the transition piece (combustion cylinder) 33, and causes the air vibration of the combustion gas flowing through the transition piece 33 to flow into the acoustic damper 1.

  According to the combustor 12, pressure fluctuation in the combustor 12 due to combustion vibration is attenuated by the acoustic part N.

  The longitudinal direction L of the acoustic damper 1 shown in FIG. 11 is arranged along the circumferential direction of the combustor 12, and the lateral direction S is arranged along the axial direction of the combustor 12. With this configuration, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the circumferential direction, as shown in FIG.

  According to the combustor 12, it is possible to prevent the occurrence of vibration that displaces in the circumferential direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  In the acoustic damper 1 shown in FIG. 11, 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. With such a configuration, as shown in FIG. 3, the acoustic damper 1 is arranged on the outer surface of the transition piece 33 mainly along the axial direction.

  According to the combustor 12, it is possible to prevent occurrence of vibration that displaces in the axial direction of the transition piece 33. Moreover, since the acoustic portion N is provided along the outer surface of the transition piece 33, the combustor 12 itself can be configured to be relatively small.

  Note that, in the acoustic damper 1 shown in FIG. 11, the longitudinal direction L may be arranged along the circumferential direction of the combustor 12, and the short direction S may be arranged 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 side direction S is arranged along the radial direction of the combustor 12, the inlet 3 </ b> A of the passage 3 is connected to the transition piece 33 so that the entrance 3 </ b> A of the passage 3 opens toward the outer surface of the transition piece 33. Adjust to extend toward the outer surface.

  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 part N is attenuated. As a result, noise and vibration during operation of the gas turbine can be reduced.

DESCRIPTION OF SYMBOLS 1 Acoustic damper 2 Housing 3 Passage 3A Inlet 3B Termination 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 cabin 17 Stator vane 18 Moving blade 20 Turbine casing 21 Stator blade 22 Moving blade 23 Exhaust diffuser 24 Rotor 25 Bearing unit 26 Bearing unit 30 Cabin housing 31 Outer cylinder 32 Inner cylinder 33 Tail cylinder 35 Pilot nozzle 36 Main nozzle 37 Gusset 38 Cabin CE combustor Axis 101 Conventional acoustic damper 103 Passage 103A Entrance 103B Terminal M Sound section

Claims (7)

An acoustic damper fixed to a vibration source and provided along an outer surface of the vibration source,
Including an inlet that takes in air vibration generated by the vibration source, and an end that becomes a resistance of the air vibration by closing the downstream side of the propagation of the air vibration, forming an acoustic part,
The acoustic section, the passage is folded back, a plurality of the passages are arranged adjacent to the periphery of the end portion, and the entrance and the end of a series of the passages are spaced apart from each other,
A single acoustic portion forming the series of passages, the passage being spirally disposed adjacent to a periphery of the end of the passage of the acoustic portion, and An inlet and the end are spaced apart;
An acoustic damper characterized by the following. An acoustic damper fixed to a vibration source and provided along an outer surface of the vibration source,
Including an inlet that takes in air vibration generated by the vibration source, and an end that becomes a resistance of the air vibration by closing the downstream side of the propagation of the air vibration, forming an acoustic part,
The acoustic section, the passage is folded back, a plurality of the passages are arranged adjacent to the periphery of the end portion, and the entrance and the end of a series of the passages are spaced apart from each other,
A plurality of the sound portions forming the series of the passages, wherein the passage of the own sound portion and the passage of the other sound portion are spirally adjacent to the periphery of the end of the passage of each sound portion; And the entrance and the end of the passage of each of the acoustic portions are disposed apart from each other,
An acoustic damper characterized by the following. 3. The acoustic damper according to claim 2 , wherein the lengths of the terminals from the entrance of each of the acoustic parts are equal. A combustor comprising the acoustic damper according to any one of claims 1 to 3 provided in a combustion cylinder, and air vibration of combustion gas flowing through the combustion cylinder flowing into the acoustic damper. A longitudinal direction of the passage of the acoustic section is arranged along a circumferential direction of the combustion cylinder, and the plurality of passages are arranged adjacent to a periphery of an end of the passage of the acoustic section in an axial direction of the combustion cylinder. The combustor according to claim 4 , wherein: A longitudinal direction of the passage of the acoustic section is arranged along an axial direction of the combustion cylinder, and a plurality of the passages are arranged adjacent to a periphery of an end of the passage of the acoustic section in a circumferential direction of the combustion cylinder. The combustor according to claim 4 , wherein: A gas turbine comprising the combustor according to any one of claims 4 to 6 .

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