JP6117612B2 - Compressor and gas turbine - Google Patents

Description

  The present invention relates to a compressor and a gas turbine provided in a gas turbine.

  Conventionally, a compressor provided in a gas turbine engine is known as a compressor (see, for example, Patent Document 1). The compressor of this gas turbine engine includes a plurality of blade stages (moving blades) and a plurality of vane stages (static blades), and the blade stages and the vane stages are alternately arranged.

JP 2006-348931 A

  By the way, in a compressor of a gas turbine, a rotor serving as a rotation shaft is arranged at the center, and a stationary blade and a moving blade are alternately arranged around the rotor in the axial direction, thereby forming an annular mainstream gas flow path. Is done. The compressor is arranged on the inner peripheral surface of the annular mainstream gas flow path so as to suppress the air compressed through the mainstream gas flow path (compressed air) from leaking between the stationary blade and the moving blade. A seal member is provided between the stationary blade and the moving blade. At this time, in order to reduce the manufacturing cost of the compressor, a seal member is provided between the stationary blade and the moving blade adjacent to the one side in the axial direction of the stationary blade. In some cases, a seal member is not provided between the moving blade adjacent to the other side in the axial direction.

  Here, a pressure wave is generated inside the mainstream gas flow path due to the disturbance of the compressed air flowing therethrough. At this time, since a clearance is formed between the moving blade and the stationary blade that are not provided with the seal member, the generated pressure wave passes through the clearance into the cavity formed inside the rotor. It can propagate and resonate with the structures in the cavity.

  Then, this invention makes it a subject to provide the compressor and gas turbine which can suppress the resonance with the structure in the cavity by a pressure wave.

  The compressor of the present invention is configured to distribute gas along an annular mainstream gas flow path formed by alternately arranging a plurality of stages of stationary blades and a plurality of stages of moving blades in the axial direction of the rotation shaft. In the compressor for compressing the gas, on the inner peripheral surface side of the mainstream gas flow path, one side in the axial direction of the stationary blade and the other side in the axial direction of the moving blade adjacent to one side of the stationary blade Between the sealing member provided between the inner surface of the mainstream gas flow path and the other axial side of the stationary blade, and the axial direction of the moving blade adjacent to the other side of the stationary blade. A plurality of projecting members provided between the other side of the stationary blade and the one side of the moving blade side or both of them and projecting in the axial direction and arranged in the radial direction. It is characterized by providing.

  According to this configuration, a plurality of projecting members can be provided between the other side in the axial direction of the stationary blade and one side in the axial direction of the moving blade. For this reason, even when a pressure wave is generated in the mainstream gas flow path, the propagation of the pressure wave can be suppressed by the plurality of protruding members, and the pressure wave passes between the stationary blade and the moving blade. Propagating into the cavity and resonating with the structure in the cavity can be suppressed.

  In addition, one axial side of the stationary blade provided with the seal member is a downstream side of the gas flow direction of the gas flowing through the mainstream gas flow path, and the stationary blade provided with a plurality of the protruding members is provided. The other side in the axial direction is preferably the upstream side in the gas flow direction.

  According to this configuration, the seal member is provided on the downstream side of the stationary blade, and the plurality of projecting members are provided on the upstream side of the stationary blade, whereby the seal member is provided on the higher compressed air pressure, and the compressed air pressure is reduced. A plurality of protruding members can be provided on the lower side. For this reason, the sealing member can suppress suitably the leakage of the compressed air with a high pressure, and can suppress the fall of compression efficiency.

  Further, it is preferable that the plurality of protruding members protrude from the other end face of the stationary blade.

  According to this configuration, there is no need to provide a plurality of projecting members on one end face of the rotor blade. For this reason, the workability of a moving blade can be improved.

  Moreover, it is preferable that each said protrusion member is formed in the cyclic | annular form continuous over the perimeter.

  According to this configuration, since the projecting member can be formed in an annular shape, the pressure wave propagates in the cavity over the entire inner circumferential surface of the annular mainstream gas flow path, and the structure in the cavity Resonance can be suppressed.

  A gas turbine according to the present invention includes the above-described compressor, a combustor that mixes compressed air compressed by the compressor and fuel to generate an air-fuel mixture, and burns the generated air-fuel mixture to generate combustion gas. And a turbine that is rotated by the generated combustion gas.

  According to this configuration, in the compressor, resonance with the structure in the cavity due to the pressure wave is not taken into consideration, so there is no need to design and manufacture in consideration of the pressure wave, and the manufacturing cost of the compressor increases. Accordingly, an increase in the manufacturing cost of the gas turbine can be suppressed.

FIG. 1 is a schematic configuration diagram of a gas turbine according to a first embodiment. FIG. 2 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the first embodiment. FIG. 3 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the second embodiment. FIG. 4 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the third embodiment. FIG. 5 is a schematic diagram around the inner shroud of the stationary blade provided in the compressor according to the fourth embodiment.

  Embodiments according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments. 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 a first embodiment. As shown in FIG. 1, the gas turbine 1 includes a compressor 11, a combustor 12, a turbine 13, and an exhaust chamber 14, and a generator (not shown) is connected to the turbine 13.

  The compressor 11 has an air intake 15 for taking in air (gas), and a plurality of stages of stationary blades 17 and a plurality of stages of moving blades 18 are alternately arranged in the axial direction in the compressor casing 16. Yes. In the compressor 11, an annular mainstream gas flow path 30 is formed by a plurality of stages of stationary blades 17 and a plurality of stages of moving blades 18 arranged alternately. The compressor 11 compresses air by circulating air along the mainstream gas flow path 30.

  The combustor 12 generates fuel 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 stages of stationary blades 21 and a plurality of stages of moving blades 22 are alternately arranged in the turbine casing 20 along the axial direction. 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 penetrate through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14. The rotor 24 is rotatably supported at the end on the compressor 11 side by the bearing portion 25, and is rotatably supported at the end on the exhaust chamber 14 side by the bearing portion 26. The rotor blades 18 and 22 are connected to the rotor 24, and a generator drive shaft (not shown) is connected to an end portion on the exhaust chamber 14 side.

  Therefore, the air taken in from the air intake port 15 of the compressor 11 circulates along the mainstream gas flow path 30 and is compressed through the plurality of stages of stationary blades 17 and the plurality of stages of moving blades 18. It becomes high temperature and high pressure compressed air. In the combustor 12, the compressed air becomes an air-fuel mixture when a predetermined fuel is supplied, and the air-fuel mixture is ignited by a burner, whereby the air-fuel mixture burns to become combustion gas. 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 plurality of moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. Then, the generator connected to the rotor 24 is driven. On the other hand, the exhaust gas that is the combustion gas after driving and rotating the rotor 24 is converted into a static pressure by the exhaust diffuser 23 in the exhaust chamber 14 and then released to the atmosphere.

  FIG. 2 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the first embodiment. In the compressor 11, a plurality of stages of stationary blades 17 and a plurality of stages of moving blades 18 are alternately arranged in the axial direction. Therefore, as shown in FIG. The moving blade 18a and the moving blade 18b are respectively arranged. The moving blade 18 a is provided on one side in the axial direction with respect to the stationary blade 17, that is, adjacent to the downstream side in the gas flow direction of air in the mainstream gas flow path 30. On the other hand, the moving blade 18 b is provided on the other side in the axial direction with respect to the stationary blade 17, that is, adjacent to the upstream side in the gas flow direction of the air in the mainstream gas flow path 30.

  The moving blade 18a and the moving blade 18b are attached to the disk 40a and the disk 40b, respectively. The disk 40a is provided on the downstream side in the gas flow direction, the disk 40b is provided on the upstream side in the gas flow direction, and a cavity 44 is formed between the disk 40a and the disk 40b. Further, a connecting portion 40c for connecting the disc 40a and the disc 40b is provided between the disc 40a and the disc 40b, and the connecting portion 40c is arranged close to the rotor 24 side (center axis I side). The disk 40a, the disk 40b, and the connecting portion 40c are integrally fixed to the rotor 24.

  A connecting hole 46 through which the spindle bolt 45 is inserted is formed in the disk 40a. The spindle bolt 45 is a fastening member for connecting a plurality of disks to which the plurality of stages of moving blades 18 and the plurality of stages of moving blades 22 are attached. A plurality of spindle bolts 45 are provided around the rotor 24, and the plurality of spindle bolts 45 are arranged at predetermined intervals in the circumferential direction. The spindle bolt 45 has a shaft portion 45 a and a head portion 45 b, and the axial direction of the shaft portion 45 a is the same as the axial direction of the rotor 24. The connecting hole 46 has a shaft portion receiving hole 46 a for receiving the shaft portion 45 a of the spindle bolt 45 and a head receiving hole 46 b for receiving the head portion 45 b of the spindle bolt 45. The head receiving hole 46b has a larger diameter than the shaft receiving hole 46a, and the head receiving hole 46b is formed on the cavity 44 side (upstream side in the gas flow direction) of the disk 40a. 46a is formed along the axial direction of the rotor 24 on the turbine side (downstream side in the gas flow direction) of the disk 40a. The spindle bolt 45 accommodated in the connecting hole 46 is covered with a cover 47 at the head 45b.

  The moving blade 18a has a blade root portion 41a attached to the disk 40a, and a blade 42a formed to extend radially outward from the blade root portion 41a. In the blade root portion 41 a, the radially outer surface constitutes a part of the inner peripheral surface of the mainstream gas channel 30. Further, the blade root portion 41 a has an end surface on one side (downstream side) in the axial direction that faces the other side (upstream side) of the stationary blade 17. Similarly, the moving blade 18b includes a blade root portion 41b attached to the disk 40a and a blade 42b formed to extend radially outward from the blade root portion 41b. In the blade root portion 41 b, the radially outer surface constitutes a part of the inner peripheral surface of the mainstream gas channel 30. Further, the blade root portion 41 b has an end surface on the other side (upstream side) in the axial direction which is a surface facing one side (downstream side) of the stationary blade 17.

  The stationary vane 17 includes an inner shroud 51, an outer shroud (not shown), and a vane 52 provided between the inner shroud 51 and the outer shroud. In the inner shroud 51, the radially outer surface constitutes a part of the inner peripheral surface of the mainstream gas flow path 30. The inner shroud 51 has an end surface on one side (downstream side) in the axial direction opposed to an end surface on the other side of the moving blade 18a, and an end surface on the other side (upstream side) in the axial direction is one side of the moving blade 18b. Opposite the end face of the side. The inner shroud 51 has a protrusion 51a that protrudes from the end surface on the upstream side in the axial direction. The protrusion 51a functions as a protrusion member described later, and protrudes toward the moving blade 18b. Further, the protrusion 51 a is located on the radially outer side of the inner shroud 51, and the upper surface thereof is a part of the inner peripheral surface of the mainstream gas flow path 30.

  On the inner peripheral surface side of the mainstream gas flow path 30, a labyrinth seal 55 as a seal member is provided between the stationary blade 17 and the moving blade 18 a adjacent to the downstream side of the stationary blade 17. The labyrinth seal 55 is provided between a radially inner surface on the downstream side of the inner shroud 51 of the stationary blade 17 and a radially outer surface on the upstream side of the disk 40a of the rotor blade 18a. The labyrinth seal 55 seals between the stationary blade 17 and the moving blade 18a, and suppresses leakage of compressed air from the mainstream gas flow path 30 to the cavity 44.

  On the inner peripheral surface side of the mainstream gas flow path 30, a plurality of protruding members 61 are provided between the stationary blade 17 and the moving blade 18 b adjacent to the upstream side of the stationary blade 17. The plurality of projecting members 61 are provided radially inward of the projecting portion 51 a of the inner shroud 51 and are arranged side by side in the radial direction. Note that, as described above, the protruding portions 51a function as the protruding members 61, and thus the plurality of protruding members 61 include the protruding portions 51a.

  The plurality of projecting members 61 are provided so as to extend in the axial direction from the downstream end face of the inner shroud 51 toward the blade root portion 41b of the rotor blade 18b. Each projecting member 61 and projecting portion 51 a are formed in an annular shape that is continuous over the entire circumference with the rotor 24 as the center. Note that, for example, two projecting members 61 are provided. For this reason, the two protruding members 61 and the protruding portions 51a are arranged concentrically. Of the two projecting members 61, one projecting member 61 is provided radially inward on the downstream end face of the inner shroud 51, and the other projecting member 61 is composed of the projecting member 61 and the projecting portion 51a on the radially inner side. Between.

  The plurality of projecting members 61 may be joined to the end surface of the inner shroud 51 by welding, or may be formed integrally with the inner shroud 51 when the inner shroud 51 is processed.

  As described above, according to the configuration of the first embodiment, the protrusion 51a is included between the upstream side of the stationary blade 17 and the downstream side of the moving blade 18b on the inner peripheral surface side of the mainstream gas flow path 30. A plurality of protruding members 61 can be provided. For this reason, even when a pressure wave is generated in the mainstream gas flow path 30, the plurality of protruding members 61 can suppress the propagation of the pressure wave and pass between the stationary blade 17 and the moving blade 18b. Thus, it is possible to suppress the pressure wave from propagating to the cavity 44 and resonating with the structure in the cavity 44. From the above, since resonance with the structure in the cavity 44 due to the pressure wave (for example, resonance of the cover 47) is not considered, there is no need to design and manufacture in consideration of the pressure wave. An increase in manufacturing cost can be suppressed.

  Further, according to the configuration of the first embodiment, the labyrinth seal 55 is provided on the downstream side of the stationary blade 17, and the plurality of protruding members 61 are provided on the upstream side of the stationary blade 17, so that the labyrinth has a higher compressed air pressure. A plurality of protruding members 61 can be provided on the side where the seal 55 is provided and the pressure of the compressed air is low. For this reason, since the labyrinth seal 55 can suitably suppress leakage of compressed air having a high pressure, the compressed air having a high pressure flows into the cavity 44 and flows from the upstream side of the stationary blade 17 to the mainstream gas flow path. Refluxing to 30 can be suppressed, and a decrease in compression efficiency can be suppressed.

  Further, according to the configuration of the first embodiment, a plurality of protruding members 61 can be provided on the upstream end face of the stationary blade 17. For this reason, it is not necessary to provide the plurality of protruding members 61 on the downstream end face of the rotor blade 18b. At this time, the disk 40a, the disk 40b, and the connecting portion 40c are integrated, and a connecting hole 46 through which the spindle bolt 45 is inserted is formed in the disk 40a. For this reason, when the connecting hole 46 is processed, since the processing of the connecting hole 46 is not hindered by the plurality of protruding members 61, the workability of the connecting hole 46 can be improved.

  In addition, according to the configuration of the first embodiment, each protruding member 61 can be formed in an annular shape, so that the pressure wave to the cavity 44 is spread over the entire circumference of the inner peripheral surface of the annular mainstream gas flow path 30. Propagation can be suppressed.

  In addition, in Example 1, although each protrusion member 61 was formed in cyclic | annular form over the perimeter, it is not limited to this structure. Each protruding member 61 does not need to be continuous over the entire inner peripheral surface of the mainstream gas flow path 30 and is discontinuous, that is, a plurality of protruding members 61 are provided at predetermined intervals in the circumferential direction. It may be done.

  In the first embodiment, the two protruding members 61 and the protruding portions 51a are provided as the plurality of protruding members, but the present invention is not limited to this configuration. A plurality of projecting members may be constituted by one projecting member 61 and projecting portions 51a. In this case, it is preferable that one protruding member 61 is provided on the radially inner side of the end face of the inner shroud 51. That is, the structure which excluded the other protrusion member 61 provided between one protrusion member 61 and the protrusion part 51a among the two protrusion members 61 may be sufficient.

  Next, the compressor 81 according to the second embodiment will be described with reference to FIG. FIG. 3 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the second embodiment. In the second embodiment, only parts different from the first embodiment will be described in order to avoid overlapping description with the first embodiment, and the same configurations as those in the first embodiment will be described with the same reference numerals. In the first embodiment, the plurality of protruding members 61 are protruded in the axial direction from the upstream side of the stationary blade 17, but in the second embodiment, the plurality of protruding members are protruded in the axial direction from the upstream side of the stationary blade 17. At the same time, it protrudes in the axial direction from the downstream side of the rotor blade 18b.

  As shown in FIG. 3, in the compressor 81 according to the second embodiment, a plurality of stationary blade side projecting members 83 are provided on the upstream end surface of the inner shroud 51 in the stationary blade 17. The plurality of stationary blade side projecting members 83 are provided radially inward of the projecting portions 51 a of the inner shroud 51 and are arranged side by side in the radial direction. Further, each stationary blade side projecting member 83 is provided to extend in the axial direction from the downstream end face of the inner shroud 51 toward the blade root portion 41b of the moving blade 18b. At this time, the stationary blade side protruding member 83 is shorter in the protruding direction than the protruding member 61 of the first embodiment. Each of the stationary blade side projecting members 83 and the projecting portions 51 a are formed in an annular shape that is continuous over the entire circumference around the rotor 24.

  A plurality of blade-side projection members 84 are provided on the downstream end face of the blade root portion 41b of the blade 18b. The plurality of blade-side projection members 84 are arranged side by side in the radial direction. The plurality of stationary blade side projecting members 83 and the plurality of moving blade side projecting members 84 are alternately arranged in the radial direction. The plurality of blade-side projection members 84 are provided to extend in the axial direction from the upstream end face of the blade root portion 41 b toward the inner shroud 51 of the stationary blade 17. Each blade-side projection member 84 is formed in an annular shape that is continuous over the entire circumference around the rotor 24. The rotor blade-side protrusion member 84 is not limited to the downstream end surface of the blade root portion 41b, and may be provided on the downstream end surface in the axial direction of the disk 40b. Further, the blade-side protrusion member 84 may be attached to the blade root portion 41b or may be attached to the disk 40b to which the blade root portion 41b is attached.

  Each of the stationary blade side projecting members 83 projecting in the axial direction and each of the stationary blade side projecting members 84 projecting in the axial direction are separated from each of the stationary blade side projecting members 83 and each of the stationary blade side projecting members 84 when the stationary blade 17 is assembled. Are formed so as not to overlap when viewed from the radial direction in order to suppress physical interference.

  As described above, according to the configuration of the second embodiment, on the inner peripheral surface side of the mainstream gas flow path 30, a plurality of stationary blade side protrusions are provided between the upstream side of the stationary blade 17 and the downstream side of the moving blade 18b. A member 83 and a plurality of blade-side projection members 84 can be provided. For this reason, even when a pressure wave is generated in the mainstream gas flow path 30, the propagation of the pressure wave can be suppressed by the plurality of stationary blade side projection members 83 and the plurality of rotor blade side projection members 84. It is possible to suppress the pressure wave from propagating to the cavity 44 through the space between the rotor 17 and the rotor blade 18 b and resonating with the structure in the cavity 44. From the above, since resonance with the structure in the cavity 44 due to the pressure wave (for example, resonance of the cover 47) is not considered, there is no need to design and manufacture in consideration of the pressure wave. An increase in manufacturing cost can be suppressed.

  Next, the compressor 91 according to the third embodiment will be described with reference to FIG. FIG. 4 is a schematic view around the inner shroud of the stationary blade provided in the compressor according to the third embodiment. In the third embodiment, only parts different from the first and second embodiments will be described in order to avoid overlapping descriptions with the first and second embodiments, and the same configuration as the first and second embodiments will be described. The same reference numerals are used for explanation. In the first embodiment, the plurality of protruding members include the two protruding members 61 and the protruding portion 51a. However, in the third embodiment, the plurality of protruding portions integrated with the inner shroud 51 as the plurality of protruding members. 92 is provided.

  As shown in FIG. 4, in the compressor 91 according to the third embodiment, a plurality of protruding portions 92 are formed so as to protrude from the upstream end face of the inner shroud 51 in the stationary blade 17. The plurality of projecting portions 92 have a triangular shape in which a cross section cut along the axial direction has a crest and a trough. The plurality of protruding portions 92 are arranged side by side in the radial direction. Further, each protruding portion 92 is formed to extend in the axial direction from the downstream end face of the inner shroud 51 toward the blade root portion 41b of the rotor blade 18b. Each protruding portion 92 is formed in an annular shape that is continuous over the entire circumference around the rotor 24.

  As described above, according to the configuration of the third embodiment, on the inner peripheral surface side of the mainstream gas flow path 30, a plurality of protruding portions 92 are provided between the upstream side of the stationary blade 17 and the downstream side of the moving blade 18b. Can be provided. For this reason, even when a pressure wave is generated in the mainstream gas flow path 30, the propagation of the pressure wave can be suppressed by the plurality of projecting portions 92, and it passes between the stationary blade 17 and the moving blade 18b. Thus, it is possible to suppress the pressure wave from propagating to the cavity 44 and resonating with the structure in the cavity 44. From the above, since resonance with the structure in the cavity 44 due to the pressure wave (for example, resonance of the cover 47) is not considered, there is no need to design and manufacture in consideration of the pressure wave. An increase in manufacturing cost can be suppressed.

  In the third embodiment, the plurality of protruding portions 92 are formed in an annular shape over the entire circumference, but the present invention is not limited to this configuration. Each projection part 92 does not need to be continuous over the entire circumference of the inner peripheral surface of the mainstream gas flow path 30, and has a discontinuous configuration, that is, a plurality of projection parts 92 are provided at predetermined intervals in the circumferential direction. It may be done. In other words, the plurality of protruding portions 92 may be provided side by side in the circumferential direction and the radial direction, may be arranged in a lattice shape, or may be arranged in a staggered manner.

  Moreover, in Example 3, although each projection part 92 was formed in triangle shape, it is not limited to this shape. The plurality of protruding portions 92 may be formed in a wave shape continuous in the radial direction, or each protruding portion 92 may be formed in a square shape.

  Next, the compressor 101 according to the fourth embodiment will be described with reference to FIG. FIG. 5 is a schematic diagram around the inner shroud of the stationary blade provided in the compressor according to the fourth embodiment. In the fourth embodiment, only parts different from the first to third embodiments will be described in order to avoid the description overlapping with the first to third embodiments, and the same components as those in the first to third embodiments will be denoted by the same reference numerals. explain. In the first embodiment, the plurality of projecting members include the two projecting members 61 and the protruding portions 51a. However, in the fourth embodiment, the plurality of projecting members include one projecting member 102 and the projecting portions 51a. It is a configuration that includes.

  As shown in FIG. 5, in the compressor 101 according to the fourth embodiment, a protruding portion 51 a protrudes from the upstream end surface of the inner shroud 51 in the stationary blade 17 and functions as a protruding member. . In addition, about the protrusion part 51a, since it is the same structure as Example 1, description is abbreviate | omitted.

  A projecting member 102 is provided on the downstream end face of the blade root 41b of the rotor blade 18b. The protruding member 102 is provided inside the protruding portion 51a in the radial direction. The protrusion 51a and the protrusion member 102 are arranged side by side in the radial direction. The protruding member 102 is provided so as to extend in the axial direction from the upstream end face of the blade root portion 41 b toward the inner shroud 51 of the stationary blade 17. The protruding member 102 is formed in an annular shape that is continuous over the entire circumference around the rotor 24. The protruding member 102 is not limited to the downstream end surface of the blade root 41b, but may be provided on the downstream end surface in the axial direction of the disk 40b. Further, the protruding member 102 may be attached to the blade root portion 41b or may be attached to the disk 40b to which the blade root portion 41b is attached.

  Further, the protruding portion 51a protruding in the axial direction and the protruding member 102 protruding in the axial direction do not overlap when viewed from the radial direction so as to suppress physical interference when the stationary blade 17 is assembled. Is formed.

  As described above, according to the configuration of the fourth embodiment, on the inner peripheral surface side of the mainstream gas flow path 30, the protrusion 51a and the protrusion are provided between the upstream side of the stationary blade 17 and the downstream side of the moving blade 18b. A member 102 can be provided. For this reason, even when a pressure wave is generated in the mainstream gas flow path 30, the propagation of the pressure wave can be suppressed by the protruding portion 51a and the protruding member 102, and between the stationary blade 17 and the moving blade 18b. It is possible to suppress the pressure wave from propagating through the cavity 44 and resonating with the structure in the cavity 44. From the above, since resonance with the structure in the cavity 44 due to the pressure wave (for example, resonance of the cover 47) is not considered, there is no need to design and manufacture in consideration of the pressure wave. An increase in manufacturing cost can be suppressed.

DESCRIPTION OF SYMBOLS 1 Gas turbine 11 Compressor 12 Combustor 13 Turbine 14 Exhaust chamber 17 Stator blade 18 Rotor blade 24 Rotor 30 Main flow gas flow path 40a, 40b Disk 40c Connection part 41a, 41b Blade root part 42a, 42b Blade 44 Cavity 45 Spindle bolt 46 Connection Hole 47 Cover 51 Inner shroud 51a Protrusion 52 Vane 55 Labyrinth seal 61 Protrusion member 81 Compressor (Example 2)
83 Stator blade side protrusion member 84 Rotor blade side protrusion member 91 Compressor (Example 3)
92 Projection part 101 Compressor (Example 4)
102 Protruding member (Example 4)

Claims (5)

A compressor that compresses the gas by circulating gas along an annular mainstream gas flow path formed by alternately arranging a plurality of stages of stationary blades and a plurality of stages of moving blades in the axial direction of the rotating shaft. In
The moving blade has a blade root portion whose outer surface in the radial direction is a part of the inner peripheral surface of the mainstream gas channel,
The stationary blade has an inner shroud in which a radially outer surface is a part of an inner peripheral surface of the mainstream gas flow path,
On the inner peripheral surface side of the mainstream gas flow path, a seal member provided between one side in the axial direction of the stationary blade and the other side of the moving blade adjacent to one side of the stationary blade;
In the inner peripheral surface side of the main gas flow path, wherein the end face of the axial direction of the other side of the inner shroud of the stationary blade, one end surface of the said blade root portion of the blades adjacent to the other side of the vane together provided, protruding toward the either or both of the end face of one side of the blade root portion of the end surface and the moving blade on the other side of the inner shroud of the vanes in the axial direction between the, in the radial direction And a plurality of projecting members provided side by side. One side in the axial direction of the stationary blade provided with the seal member is a downstream side in the gas flow direction of the gas flowing through the mainstream gas flow path,
2. The compressor according to claim 1, wherein the other side in the axial direction of the stationary blade provided with the plurality of protruding members is an upstream side in the gas flow direction.   The compressor according to claim 1, wherein the plurality of protruding members protrude from an end surface on the other side of the stationary blade.   The compressor according to any one of claims 1 to 3, wherein each of the protruding members is formed in an annular shape that is continuous over the entire circumference. The compressor according to any one of claims 1 to 4,
A combustor that mixes compressed air and fuel compressed by the compressor to generate an air-fuel mixture, and burns the generated air-fuel mixture to generate combustion gas;
A gas turbine comprising: a turbine that is rotated by generated combustion gas.

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