Rotating Machinery

Abstract

To provide a rotary machine capable of further reducing vibration.SOLUTION: A rotary machine includes: a rotating shaft rotating around an axis; a plurality of moving blades aligned in a circumferential direction on an outer peripheral side of the rotating shaft and having a blade root, a platform, and a blade body; and a damper member arranged inside the platform in a radial direction. The platform has a first end face oriented to one side in the circumferential direction, and a second end face opposing the first end face of the other adjacent platform by being oriented to the other side in the circumferential direction. The damper member has a first damper provided on the first end face and having a first abutment face, a second damper having a second abutment face brought into slide contact with the first abutment face of the first damper and capable of abutting on the second end face, and an elastic member for connecting the first damper and the second damper.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present disclosure relates to rotary machines. [Background technology]

[0002] In rotary machines such as gas turbines and jet engines, a damper is provided between each pair of adjacent turbine rotor blades. The damper comes into contact with the turbine rotor blades when the rotary machine rotates. When an exciting force acts on the turbine rotor blades, causing vibration, the vibration is damped by friction at the contact points between the damper and the turbine rotor blades. For example, Patent Document 1 discloses a rotary machine equipped with a cylindrical damper pin that comes into contact with both platforms of adjacent turbine rotor blades. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2016-217349 Summary of the Invention [Problem to be solved by the invention]

[0004] However, the above-described damper pins wear over time. As the wear progresses, the cross-sectional shape of the damper pin becomes polygonal, which may cause the damper pin to lose its vibration damping characteristics. As a result, vibrations are not damped, affecting the operation of the rotating machine.

[0005] The present disclosure has been made to solve the above-mentioned problems, and has an object to provide a rotating machine with further reduced vibrations. [Means for solving the problem]

[0006] In order to solve the above problems, the rotary machine according to the present disclosure includes a rotary shaft that rotates around an axis line, a plurality of blade roots that are arranged in a circumferential direction on the outer periphery side of the rotary shaft and attached to the rotary shaft, a platform provided radially outward of the blade root, and a blade body that extends radially outward from the platform, and a rotor blade having a rotor shaft and a rotor blade base. Between the platforms and a damper member provided on the platform, wherein the platform has a first end face facing one circumferential side and extending radially, and a second end face facing the other circumferential side, opposing the first end face of another adjacent platform, and extending radially outward to the other circumferential side, and the damper member has a first damper provided on the first end face and having a first abutment surface, a second damper having a second abutment surface in sliding contact with the first abutment surface of the first damper and capable of abutting against the second end face, and an elastic member connecting the first damper and the second damper. [Effects of the Invention]

[0007] According to the present disclosure, it is possible to provide a rotary machine with further reduced vibration. [Brief explanation of the drawings]

[0008] [Figure 1] 1 is a schematic cross-sectional view showing a configuration of a gas turbine according to a first embodiment of the present disclosure. FIG. [Figure 2] FIG. 2 is a schematic view of a rotor blade according to the first embodiment of the present disclosure, viewed from the axial direction. [Figure 3] FIG. 2 is an enlarged cross-sectional view of a main portion of the platform according to the first embodiment of the present disclosure. [Figure 4] FIG. 2 is an enlarged cross-sectional view of the damper member according to the first embodiment of the present disclosure. [Figure 5] FIG. 10 is a perspective view of a damper member according to a second embodiment of the present disclosure. [Figure 6] FIG. 10 is a perspective view showing a modified example of a damper member according to the second embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0009] First Embodiment (Gas turbine configuration) A gas turbine 1 (rotary machine) according to a first embodiment of the present disclosure will be described below with reference to FIGS.

[0010] As shown in FIG. 1, the gas turbine 1 according to this embodiment includes a compressor 2 that generates compressed air, a combustor 9 that generates combustion gas by mixing fuel with the compressed air and burning the fuel, and a turbine 10 that is driven by the combustion gas.

[0011] The compressor 2 has a compressor rotor 3 that rotates about an axis O, and a compressor casing 4 that covers the compressor rotor 3 from the outer periphery. The compressor rotor 3 has a columnar shape that extends along the axis O. A plurality of compressor rotor blade stages 5 are provided on the outer periphery of the compressor rotor 3 and are arranged at intervals in the direction of the axis O. Each compressor rotor blade stage 5 has a plurality of compressor rotor blades 6 that are arranged on the outer periphery of the compressor rotor 3 at intervals in the circumferential direction of the axis O.

[0012] The compressor casing 4 has a cylindrical shape centered on the axis O. A plurality of compressor stator vane stages 7 are provided on the inner circumferential surface of the compressor casing 4 and arranged at intervals in the direction of the axis O. These compressor stator vane stages 7 are arranged alternately with the compressor rotor blade stages 5 when viewed from the direction of the axis O. Each compressor stator vane stage 7 has a plurality of compressor stator vanes 8 arranged on the inner circumferential surface of the compressor casing 4 at intervals in the circumferential direction of the axis O.

[0013] The combustor 9 is provided between the compressor casing 4 and a turbine casing 12, which will be described later. Compressed air generated by the compressor 2 is mixed with fuel inside the combustor 9 to form premixed gas. This premixed gas is combusted inside the combustor 9 to generate high-temperature, high-pressure combustion gas. The combustion gas is guided into the turbine casing 12 to drive the turbine 10.

[0014] The turbine 10 has a turbine rotor 11 (rotating shaft) that rotates about an axis O, a turbine casing 12 that covers the turbine rotor 11 from the outer periphery, and a damper member 50 (described later). The turbine rotor 11 has a columnar shape extending along the axis O. A plurality of turbine blade stages 20 are arranged at intervals in the direction of the axis O on the outer periphery of the turbine rotor 11. Each turbine blade stage 20 has a plurality of turbine blades 30 that are arranged at intervals in the circumferential direction of the axis O on the outer periphery of the turbine rotor 11. The turbine rotor 11 is integrally connected to the compressor rotor 3 in the direction of the axis O to form a gas turbine rotor 101.

[0015] The turbine casing 12 has a cylindrical shape centered on the axis O. A plurality of turbine stator vane stages 13 are provided on the inner peripheral surface of the turbine casing 12 and arranged at intervals in the direction of the axis O. These turbine stator vane stages 13 are arranged alternately with respect to the turbine rotor blade stages 20 when viewed from the direction of the axis O. Each turbine stator vane stage 13 has a plurality of turbine stator vanes 14 arranged at intervals in the circumferential direction of the axis O on the inner peripheral surface of the turbine casing 12. The turbine casing 12 is connected to the compressor casing 4 in the direction of the axis O to form a gas turbine casing 102. That is, the gas turbine rotor 101 is rotatable integrally with the gas turbine casing 102 about the axis O.

[0016] (Configuration of turbine blades) Next, the turbine rotor blade 30 will be described in more detail with reference to Figure 2. The turbine rotor blade 30 has a blade root 31, a platform 32, and a blade body 41. The blade root 31 is the portion of the turbine rotor blade 30 that is attached to the turbine rotor 11. The turbine rotor 11 is composed of a plurality of circular disks centered on the axis O, stacked in the direction of the axis O. The blade root 31 is attached integrally to the disk by being fitted from the direction of the axis O into a recessed groove (not shown) formed on the outer circumferential surface of the disk. In this way, the turbine rotor blades 30 are arranged radially with a circumferential gap between them.

[0017] The platform 32 is provided integrally with the blade root 31 on the radially outer side. The platform 32 protrudes in the axial direction and the circumferential direction from the radially outer end of the blade root 31. An outer peripheral surface 33 of the platform 32 facing radially outward is exposed to the combustion gas passing through the turbine 10.

[0018] The surface of the platform 32 facing one circumferential side is a first side surface 70 (first end surface). The surface of the platform 32 facing the other circumferential side is a second side surface 60. Between adjacent platforms 32, the first side surface 70 of one platform 32 faces the second side surface 60 of the other platform 32 at a circumferential interval. A recess 90 recessed toward one circumferential side is formed in the second side surface 60. A damper member 50 is housed between this recess 90 and the first side surface 70 facing the recess 90.

[0019] (Configuration of damper member) Next, the damper member 50 and its surrounding configuration will be described in detail with reference to Figure 3. As shown in the figure, the first side surface 70 of the platform 32 extends in the radial direction and the axial direction O. The second side surface 60 has an outer peripheral end surface 61, a second end surface 62, a bottom surface 63, a third end surface 64, and an inner peripheral end surface 65.

[0020] The outer peripheral end surface 61 extends radially inward from the edge of the outer peripheral surface 33. The outer peripheral end surface 61 faces the first side surface 70 at a distance in the circumferential direction. The second end surface 62 extends radially inward from the radially inner edge of the outer peripheral end surface 61. More specifically, the second end surface 62 extends so as to incline toward one circumferential side as it extends radially inward.

[0021] The bottom surface 63 extends radially inward from the radially inner edge of the second end surface 62. The third end surface 64 extends radially inward from the radially inner edge of the bottom surface 63 toward the other circumferential side. The second end surface 62, the bottom surface 63, and the third end surface 64 form the recess 90 described above. The inner circumferential end surface 65 extends radially inward from the other circumferential edge of the third end surface 64. The inner circumferential end surface 65 faces the first side surface 70 with a circumferential gap therebetween.

[0022] The damper member 50 has a first damper 51, a second damper 52, and an elastic member 53 that connects the first damper 51 and the second damper 52. The first damper 51 is detachably fixed to the first side surface 70. The first damper 51 has a triangular shape when viewed from the direction of the axis O. As shown in FIG. 4 , the first damper 51 has a fixing surface 54, an outer surface 57, a magnet 55, and a first contact surface 56.

[0023] The surface of the first damper 51 that abuts against the first side surface is a fixed surface 54. A magnet 55 is embedded in the fixed surface 54. The first damper 51 is detachably attached to the first side surface by the magnetic force of the magnet 55. Note that the magnetic force of the magnet 55 is desirably strong enough to fix the first damper 51 on the first side surface 70 so that it cannot be relatively displaced.

[0024] The outer surface 57 faces radially outward. The first contact surface 56 connects the radially inner edge of the fixing surface 54 and the edge of the outer surface 57 on one side in the circumferential direction.

[0025] The first contact surface 56 has a first region 81, a second region 83, and a pressure-receiving region 82. The first region 81 is located on one circumferential side of the first contact surface 56. The first region 81 extends radially inward as it moves from one circumferential side to the other circumferential side. The second region 83 extends in the same direction as the first region 81 and is located on the other circumferential side of the first region 81. The second region 83 is located radially inward of the first region 81. In other words, a step is formed between the second region 83 and the first region 81. This step is defined as the pressure-receiving region 82. The pressure-receiving region 82 extends in a direction intersecting the first region 81 and the second region 83.

[0026] The second damper 52 has a second contact surface 58 that is in sliding contact with the first contact surface 56 of the first damper 51, and an arcuate surface 84 that can come into contact with the second end face 62. The second contact surface 58 has a third region 85, a fourth region 86, and a pressurized region 87. The third region 85 is located on one circumferential side of the second contact surface 58. The third region 85 is in contact (surface contact) with the first region 81. The fourth region 86 extends in the same direction as the third region 85 and is located on the other circumferential side of the third region 85. The fourth region 86 is in contact (surface contact) with the second region 83. The fourth region 86 is located radially inward of the third region 85. In other words, a step is formed between the fourth region 86 and the third region 85. This step is the pressurized region 87. The pressure region 87 extends in a direction intersecting the third region 85 and the fourth region 86 .

[0027] A space having a rectangular cross section is formed by the four surfaces of the first region 81, the pressure-receiving region 82, the pressure-applying region 87, and the fourth region 86. This space is filled with an elastic member 53. A resin material containing hard rubber is preferably used as the elastic member 53. In other words, this elastic member 53 has higher elasticity and viscosity than the materials forming the first damper 51 and the second damper 52. The elastic member 53 also has adhesive force for connecting the first damper 51 and the second damper 52 together.

[0028] The arcuate surface 84 connects the radially outer edge of the third region 85 and the radially inner edge of the fourth region 86. The arcuate surface 84 has an arc shape that is convex toward one circumferential side and toward the radially inner side. The arcuate surface 84 is capable of coming into contact with the second end face 62.

[0029] (Action and effect) Next, the operation of the damper member 50 will be described with reference to Fig. 3 or 4. When the gas turbine 1 is operated, vibrations may occur in the turbine rotor blades 30 in the circumferential direction. In other words, the turbine rotor blades 30 may vibrate so as to fall from one circumferential side to the other. The damper member 50 is provided to absorb and attenuate such vibrations.

[0030] When the turbine rotor blade 30 is displaced in the circumferential direction, the platform 32 is also displaced in the circumferential direction accordingly. As a result, the second end surface 62 of the recess 90 comes into contact with the second damper 52 of the damper member 50. Specifically, the second end surface 62 presses against the arc surface 84 of the second damper 52. As a result, the second damper 52 slides relative to the first damper 51.

[0031] As the second damper 52 slides, frictional forces are generated between the third region 85 and the first region 81 and between the fourth region 86 and the second region 83. That is, the energy of vibrations generated in the platform 32 is converted into thermal energy (frictional heat) due to friction. As a result, the vibrations can be damped. Therefore, the gas turbine 1 can be operated stably.

[0032] Furthermore, an elastic member 53 is provided between the first damper 51 and the second damper 52. When the second damper 52 slides, the elastic member 53 is elastically deformed so as to be crushed between the pressure application area 87 and the pressure receiving area 82. When this elastic deformation occurs, part of the vibration energy of the platform 32 is absorbed. Therefore, in addition to the vibration damping effect due to friction described above, it is possible to further effectively damp vibration.

[0033] Furthermore, with the above configuration, the first abutment surface 56 and the second abutment surface 58 extend radially inward from one circumferential side to the other. In other words, these surfaces extend in a direction following the displacement of the second end surface 62 due to vibration. This allows the force generated by the displacement of the second end surface 62 to be efficiently converted into sliding between the first abutment surface 56 and the second abutment surface 58. As a result, a sufficient frictional force can be generated between the first abutment surface 56 and the second abutment surface 58. This makes it possible to obtain a sufficient vibration damping effect.

[0034] In addition, according to the above configuration, the first damper 51 is detachably fixed to the first side surface 70 by the magnet 55. This makes it possible to easily add the damper member 50 to an existing turbine rotor blade 30 simply by attaching the magnet 55. Furthermore, when the damper member 50 becomes worn, it can be easily removed and replaced with a new damper member 50. This makes it possible to operate the gas turbine 1 more stably.

[0035] Furthermore, according to the above configuration, the second damper 52 is formed with an arcuate surface 84. This arcuate surface 84 abuts against the second end face 62. Even if the amount of displacement due to vibration of the turbine rotor blade changes, that is, even if the abutment angle or attitude of the second end face 62 with respect to the arcuate surface 84 changes, the arcuate shape of the arcuate surface 84 makes it possible to absorb the change in displacement in response to any abutment angle. This makes it possible to damp vibration even more effectively.

[0036] (Other embodiments) The above describes in detail the embodiments of the present disclosure with reference to the drawings, but the specific configuration is not limited to this embodiment, and design changes and the like are also included within the scope that does not deviate from the gist of the present disclosure. In the above embodiment, the first damper 51 is fixed to the first side surface by the magnet 55. However, the first damper 51 does not necessarily have to be fixed by the magnet 55, and may be fixed to the platform 32 by welding or bolting.

[0037] Furthermore, the elastic member 53 may be disposed at a position different from the above configuration, as long as it can connect the first damper 51 and the second damper 52.

[0038] Second Embodiment Next, a second embodiment of the present disclosure will be described with reference to Fig. 5. Note that the same components as those in the first embodiment are denoted by the same reference numerals, and detailed description thereof will be omitted.

[0039] 5, in the damper member 150 according to this embodiment, the first damper 151 and the second damper 152 are divided into two in the direction of the axis O. Specifically, the first damper 151 has a plurality (a pair) of first damper segments 151a, and the second damper 152 has a plurality (a pair) of second damper segments 152a.

[0040] The first damper segments 151a abut against each other via first dividing surfaces 91 (dividing surfaces) extending in the circumferential direction. The second damper segments 152a abut against each other via second dividing surfaces 92 (dividing surfaces). When viewed in the circumferential direction, the second dividing surface 92 has a first radial surface 93 that extends radially and is located on the outer circumferential side, an axial surface 94 that extends from an inner circumferential edge of the first radial surface 93 in the direction of the axis O, and a second radial surface 95 that extends radially inward from an edge of the axial surface 94. In other words, when viewed in the circumferential direction, the second dividing surface 92 extends in a zigzag shape in the radial direction and in the direction of the axis O.

[0041] The above-mentioned first divided surface 91 and second divided surface 92 refer to imaginary surfaces formed between the first damper divided bodies 151a and between the second damper divided bodies 152a, respectively.

[0042] (Action and effect) In addition to the circumferential vibration described in the first embodiment, the turbine rotor blade 30 also experiences a vibration mode in which the turbine rotor blade 30 itself is twisted in the direction of the axis O. In other words, this is a vibration mode in which both ends of the turbine rotor blade 30 in the chord direction are displaced in directions separating from each other. When such vibration occurs, in the damper member 150 according to this embodiment, the first damper segment 151a and the second damper segment 152a are displaced relative to each other so as to slide against each other on their respective dividing surfaces (first dividing surface 91, second dividing surface 92).

[0043] As a result, the vibration energy is converted into heat (frictional heat) due to friction between the first damper segments 151a and between the second damper segments 152a. As a result, it is possible to attenuate the vibration energy. That is, in addition to the circumferential vibration described in the first embodiment, a high damping effect can be achieved also against the torsional vibration described above. This allows the gas turbine 1 to be operated more stably.

[0044] Furthermore, as described above, the second divided surface 92 of the second damper 152 extends in a zigzag pattern in the radial direction and the direction of the axis O. This ensures a larger contact area between the second damper divided bodies 152a than when the second divided surface 92 simply extends in the radial direction, for example. As a result, it is possible to further enhance the vibration damping effect due to friction described above.

[0045] The second embodiment of the present disclosure has been described above. Note that various changes and modifications can be made to the above configuration without departing from the spirit and scope of the present disclosure.

[0046] For example, as shown as a modified example in Fig. 6, a second elastic member 153 can be further provided on the second divided surface 92. Specifically, an example in which the second elastic member 153 is provided between the axial surfaces 94 is conceivable. As with the elastic member 53, a resin material containing hard rubber is preferably used for this second elastic member 153. In other words, this second elastic member 153 has higher elasticity and viscosity than the materials forming the first damper 151 and the second damper 152. The second elastic member 153 also has adhesive force for bonding the second damper divided bodies 152a together.

[0047] According to this configuration, in addition to the vibration damping effect due to the friction between the second damper segments 152a, it is also possible to obtain the vibration energy absorption effect due to the elastic deformation of the second elastic member 153. As a result, it is possible to further reduce vibration.

[0048] <Other embodiments> In addition to the above-described embodiments, the following configurations may be adopted. In the above-described second embodiment, the first damper 151 has a pair of first damper segments 151a, and the second damper 152 has a pair of second damper segments 152a. However, the number of segments of the first damper 151 and the second damper 152 is not limited to two and may be three or more. In other words, two or more first segmented surfaces 91 and two or more second segmented surfaces 92 may be formed. As the number of segments increases, the first damper 151 and the second damper 152 can more flexibly follow torsional vibrations (deformations) of the turbine rotor blade 30 itself. As a result, vibrations can be damped more effectively.

[0049] <Additional Notes> The rotating machine described in each embodiment can be understood, for example, as follows.

[0050] (1) A rotary machine (gas turbine 1) according to a first aspect includes a rotating shaft (turbine rotor 11) that rotates around an axis O, a plurality of blade roots 31 that are arranged in a circumferential direction on the outer periphery of the rotating shaft and attached to the rotating shaft, platforms 32 that are provided radially outward of the blade roots 31, and rotor blades (turbine rotor blades 30) that have blade bodies 41 that extend radially outward from the platforms 32, and damper members 50 that are provided radially inward of the platforms 32 between adjacent rotor blades, and the platforms 32 face one side in the circumferential direction. and a second end face 62 that faces the other side in the circumferential direction, thereby facing the first end face of the adjacent platform 32, and extends toward the other side in the circumferential direction as it moves radially outward. The damper member 50 includes a first damper 51 that is provided on the first end face and has a first abutment surface 56, a second damper 52 that has a second abutment surface 58 that is in sliding contact with the first abutment surface 56 of the first damper 51 and can abut against the second end face 62, and an elastic member 53 that connects the first damper 51 and the second damper 52.

[0051] According to the above configuration, the friction generated when the second damper 52 slides against the first damper 51 and the elastic force of the elastic member 53 can damp vibration of the rotor blades.

[0052] (2) A rotary machine according to a second aspect is a rotary machine according to (1), in which the first abutment surface 56 and the second abutment surface 58 extend radially inward from one circumferential side to the other circumferential side.

[0053] According to the above configuration, a sufficient friction force can be generated between the first contact surface 56 and the second contact surface 58 when vibration occurs in the rotor blade.

[0054] (3) A rotating machine according to a third aspect is a rotating machine according to (1) or (2), wherein the first contact surface 56 has a first region 81 located on one circumferential side, a second region 83 located on the other circumferential side of the first region 81 and radially inward from the first region 81, and a pressure-receiving region 82 connecting the first region 81 and the second region 83, the second contact surface 58 has a third region 85 located on one circumferential side, a fourth region 86 located on the other circumferential side of the third region 85 and radially inward from the third region 85, and a pressure-receiving region 87 connecting the third region 85 and the fourth region 86, and the elastic member 53 is arranged in a space formed by the first region 81, the pressure-receiving region 82, the pressure-receiving region 87, and the fourth region 86.

[0055] According to the above configuration, the elastic member 53 is elastically deformed so as to be crushed between the pressure region 87 and the pressure-receiving region 82, thereby making it possible to effectively absorb and attenuate the vibration energy of the rotor blades.

[0056] (4) A rotating machine according to a fourth aspect is a rotating machine according to any one of aspects (1) to (3), further comprising a magnet 55 that fixes the first damper 51 to the first end face of the platform.

[0057] According to the above configuration, the magnet 55 makes it possible to easily add a damper member to an existing rotor blade.

[0058] (5) A rotary machine according to a fifth aspect is a rotary machine according to any one of aspects (1) to (4), in which the portion of the second damper 52 facing the second end face has an arc-shaped cross-sectional shape.

[0059] According to the above configuration, even if the amount of displacement due to vibration of the rotor blade changes, the change in the displacement can be absorbed by the arcuate surface 84.

[0060] (6) A rotating machine according to a sixth aspect is a rotating machine according to any one of aspects (1) to (5), wherein the first damper 51 and the second damper 52 have a plurality of first damper segments 151a and a plurality of second damper segments 152a that are divided in the axial direction and can slide against each other via the dividing surfaces.

[0061] According to the above configuration, even if vibrations that twist the rotor blade in the axial direction occur, the first damper segment 151a and the second damper segment 152a can slide on their dividing surfaces to absorb and damp the vibrations.

[0062] (7) A rotary machine according to a seventh aspect is the rotary machine of (6), further including a second elastic member 153 disposed between the second damper segments 152a.

[0063] According to the above configuration, the second elastic member 153 can further absorb and attenuate the energy of the torsional vibration. [Explanation of symbols]

[0064] 1...Gas turbine (rotating machine) 2...Compressor 3...Compressor rotor 4...Compressor casing 5...Compressor rotor blade stage 6...Compressor rotor blade 7...Compressor stator vane stage 8...Compressor stator vane 9...Combustor 10...Turbine 11...Turbine rotor 12...Turbine casing 13...Turbine stator blade stage 14...Turbine vane 20...Turbine blade stage 30...Turbine blade 31...wing root 32...Platform 33…Outer surface 41...Wing body 50...Damper member 51...First damper 52...Second damper 53...Elastic member 54…Fixed surface 55...Magnet 56...First contact surface 57...External surface 58...Second contact surface 60…Second side 61...Outer peripheral end face 62…Second end face 63...Bottom 64…Third end face 65...Inner peripheral end face 70...First side (first end surface) 81…First area 82…Pressure area 83…Second area 84...Arc surface 85…Third area 86...Fourth area 87...Pressure area 90...recess 91...first dividing plane 92…Second dividing plane 93…First radial plane 94...Axial surface 95…Second radial surface 101...Gas turbine rotor 102...Gas turbine casing 150...Damper member 151...First damper 152...Second damper 151a...First damper division body 152a...Second damper segment 153...Second elastic member O…Axis line

Claims

1. A rotation shaft that rotates around an axis line, a plurality of rotor blades arranged in a circumferential direction on the outer circumferential side of the rotary shaft, the rotor blades having blade roots attached to the rotary shaft, platforms provided radially outward of the blade roots, and blade bodies extending radially outward from the platforms; a damper member provided between the platforms of the adjacent rotor blades; Equipped with The platform comprises: a first end surface facing one side in the circumferential direction and extending in the radial direction; a second end surface that faces the other side in the circumferential direction, thereby facing the first end surface of another adjacent platform, and extends toward the other side in the circumferential direction as it moves radially outward; and The damper member is a first damper provided on the first end surface and having a first contact surface; a second damper having a second contact surface that is in sliding contact with the first contact surface of the first damper and that is capable of contacting the second end surface; an elastic member connecting the first damper and the second damper; A rotating machine having a

2. The rotary machine according to claim 1 , wherein the first contact surface and the second contact surface extend radially inward from one circumferential side to the other circumferential side.

3. the first contact surface has a first region located on one circumferential side, a second region located on the other circumferential side of the first region and provided radially inward of the first region, and a pressure-receiving region connecting the first region and the second region, the second contact surface has a third region located on one circumferential side, a fourth region located on the other circumferential side of the third region and radially inward of the third region, and a pressure region connecting the third region and the fourth region, The rotary machine according to claim 1 or 2, wherein the elastic member is disposed in a space formed by the first region, the pressure-receiving region, the pressure-applying region, and the fourth region.

4. The rotary machine according to claim 1 , further comprising a magnet that fixes the first damper to the first end surface of the platform.

5. The rotary machine according to claim 1 , wherein a portion of the second damper facing the second end surface has an arc-shaped cross section.

6. 6. The rotary machine according to claim 1, wherein the first damper and the second damper have a plurality of first damper segments and a plurality of second damper segments that are divided in the axial direction and are slidable relative to each other via a dividing surface.

7. The rotary machine according to claim 6 , further comprising a second elastic member disposed between the second damper segments.

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