JP2019173650A - Rotary machine - Google Patents

Abstract

To provide a rotary machine capable of improving its anti-fluttering characteristic.SOLUTION: There are provided a revolving shaft rotated around an axis line, several moving blades arranged in a peripheral direction at an outside of the revolving shaft, the moving blades having blade roots attached to the revolving shaft, a platform arranged outside in a radial direction of said roots, a blade main body extending outside in a radial direction from said platform and several damper members 50A, 50B arranged between the moving blades adjacent to each other and having surfaces abutted against both platforms of these adjoining moving blades, and these damper members 50A, 50B have different structures.SELECTED DRAWING: Figure 3

Description

  The present invention relates to a rotating machine.

In a rotating machine such as a gas turbine or a jet engine, a configuration in which a damper is provided between adjacent turbine blades is known. The damper contacts the turbine rotor blade when the rotating machine rotates. When vibration is generated by the excitation force acting on the turbine blade, the vibration is attenuated by the frictional force at the contact point between the damper and the turbine blade.
For example, Patent Document 1 discloses a rotary machine including a damper pin that contacts both platforms of adjacent turbine blades.

JP, 2006-217349, A

By the way, a vibration phenomenon called flutter may occur during start-up of a rotary machine equipped with turbine blades or during high-load operation. In order to suppress the flutter effectively, it is necessary to give vibration damping to a wide range of excitation forces.
However, in a rotating machine having a general damper, the plurality of dampers have the same structure as each other, and the range of excitation force that can effectively exhibit vibration damping is limited.

  This invention is made | formed in view of such a situation, Comprising: It aims at providing the rotary machine which can improve flutter resistance.

The present invention employs the following means in order to solve the above problems.
That is, a rotating machine according to an aspect of the present invention includes a rotating shaft that rotates about an axis, and a plurality of moving blades arranged in the circumferential direction on the outer peripheral side of the rotating shaft, the blades attached to the rotating shaft A moving blade having a root, a platform provided radially outside the blade root, and a blade body extending radially outward from the platform, and the moving blades adjacent to each other. A plurality of damper members whose surfaces abut against both of the wing platforms, and at least one of the plurality of damper members has a different structure from the other damper members.

  According to such a rotating machine, the structure of some damper members among the plurality of damper members is different, so that the contact mode between the damper member and the platform is different for each damper member. Therefore, attenuation can be effectively exhibited in a wide range of excitation force.

  In the rotating machine, the friction coefficient of the surface of at least one of the plurality of damper members may be different from the friction coefficient of the surface of the other damper member.

  Thereby, the friction characteristics at the time of contact between the damper member and the platform are different for each damper member. Therefore, the timing at which each damper member that comes into contact with the platform during rotation begins to slide is different. Thereby, attenuation can be effectively exhibited in a wide range of excitation force.

  In the rotating machine, the damper member includes a damper member main body and a coating layer that covers an outer surface of the damper member main body, and the coating layer of at least one of the damper members is a plurality of the damper members. The material may be different from the material of the coating layer of the other damper member.

  As a result, the friction coefficient of the surface of each damper member can be easily adjusted, and a wide range of excitation forces can be easily accommodated.

  In the rotating machine, the weight of at least one of the plurality of damper members may be different from the weight of the other damper members.

  As a result, when the centrifugal force acts on each damper member, the pressing load from the damper member to the platform is different for each damper member. Thereby, the friction characteristic for each damper member can be changed, and the restoring characteristic for each damper member can be changed. Therefore, it becomes possible to deal with a wide range of excitation forces.

  In the rotary machine, the damper member has a damper member main body formed of a base material, and the material of the base material of at least one of the damper member main bodies is the other damper member. The material of the base material of the damper member main body may be different.

  When the material of the base material of the damper member is different, the density of each damper member is different. Thereby, the pressing load from the damper member to the platform when a centrifugal force acts on each damper member can be changed. Therefore, it is possible to apply attenuation to a wide range of excitation forces as the entire rotating machine. Further, when the base material of the damper member is exposed on the surface, it is possible to exert a frictional force based on the friction coefficient for each material of the base material.

  In the rotating machine, the damper member has a pin shape extending in the axial direction, and an outer diameter of at least one of the plurality of damper members is equal to an outer diameter of the other damper member. May be different.

  When the diameter of the damper member is different, the weight of each damper member is different, and the contact portion of the damper member on the platform is different for each platform. As a result, attenuation can be applied to a wide range of excitation forces.

  In the rotating machine, the damper member has a pin shape extending in the axial direction, and is composed of a plurality of divided pins connected in the axial direction. At least one of the damper members may be composed of a combination of the split pins different from the other damper members.

  This also makes it possible to easily adjust the friction coefficient and weight of each damper member. Therefore, it is possible to easily cope with a wide range of excitation forces.

  In the rotating machine, the damper member has a damper main body extending in the axial direction, and a coating layer covering only a part of the outer peripheral surface of the damper main body in the axial direction, and among the plurality of the damper members The axial position of the coating layer of the at least one damper member may be different from the axial position of the coating layer of the other damper member.

  Here, the amplitude of the damper member may not be uniform in the axial direction depending on the vibration mode shape. As a result, wear at the axial position where the amplitude of the damper member is large increases. In this aspect, the wear of the damper member can be suppressed by forming the coating layer only in the axial direction position where the amplitude increases in this way. In addition, by changing the axial position of the coating for each damper pin, the vibration characteristics for each damper pin can be changed, and a wide range of excitation forces can be handled.

  A rotating machine according to one aspect of the present invention includes a rotating shaft that rotates about an axis, and a plurality of moving blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, the blade root being attached to the rotating shaft A blade provided on the radially outer side of the blade root, a blade having a blade body extending radially outward from the platform, and the blades adjacent to each other provided between the blades adjacent to each other. A plurality of damper members whose surfaces abut against both of the damper abutting surfaces of the platform, and the friction coefficient of the damper abutting surface with which at least one of the plurality of damper members abuts is other than It differs from the friction coefficient of the damper contact surface with which the damper member contacts.

  Thereby, the friction characteristics at the time of contact between the damper member and the platform are different for each damper member. Therefore, the timing at which each damper member that comes into contact with the platform during rotation begins to slide is different. Thereby, attenuation can be exhibited in a wide range of excitation force.

  In the rotating machine of the above aspect, the damper contact surface is formed by a coating layer laminated on the surface of the platform, and the damper contact surface on which at least one of the plurality of damper members contacts is formed on the damper contact surface. The friction coefficient of the coating layer may be different from the friction coefficient of the coating layer on the damper contact surface with which the other damper member contacts.

  As a result, the friction coefficient of the surface for each platform can be easily adjusted, and a wide range of excitation forces can be easily accommodated.

  In the rotary machine of the above aspect, a part of the damper contact surface is formed by a coating layer laminated on the surface of the platform, and at least one of the damper members contacts the damper member. The axial position of the coating layer on the damper contact surface may be different from the axial position of the coating layer on the damper contact surface with which the other damper member contacts.

  Here, the amplitude of the damper member may not be uniform in the axial direction depending on the vibration mode shape. Therefore, the wear of the platform becomes large at the axial position where the amplitude of the damper member is large. In the present aspect, platform wear can be suppressed by forming the coating layer only in the axial direction position where the amplitude increases in this way. In addition, by changing the position of the coating in the axial direction for each platform, it is possible to change the vibration characteristics of each damper member in contact with the platform, and it is possible to deal with a wide range of excitation forces.

  A rotating machine according to one aspect of the present invention includes a rotating shaft that rotates about an axis, and a plurality of moving blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, the blade root being attached to the rotating shaft A blade body extending radially outward from the blade root, and a moving blade having a shroud provided at an end on the radially outer side of the blade body, wherein the shrouds are adjacent to each other between the adjacent shrouds. A contact surface that forms a friction damper by contact, and the friction force generated in at least one of the plurality of friction dampers is different from the friction force in the other friction damper. Yes.

  Since the friction characteristics of each friction damper are different, vibration damping can be given to a wide range of excitation forces.

  In the rotating machine of the above aspect, the contact surface is formed by a coating layer laminated on the surface of the shroud, and the friction coefficient of the coating layer of at least one of the friction dampers is the friction layer. The friction coefficient of the coating layer of the other friction damper may be different.

  As a result, the friction characteristics for each friction damper can be easily varied, and a wide range of excitation forces can be easily accommodated.

  According to the rotating machine of the present invention, the flutter resistance can be improved.

It is a typical longitudinal section of the gas turbine concerning a first embodiment. It is the typical figure which looked at the moving blade group of the gas turbine which concerns on 1st embodiment from the axial direction. (A), (b) is a figure which shows the state which the damper pin which has a coating layer which consists of a different material is contact | abutting to the platform. It is a figure explaining the 1st modification of 1st embodiment, Comprising: (a), (b) is a figure which shows the state which the damper pin which consists of a base material of a different material contact | abuts to a platform. It is a figure explaining the 2nd modification of 1st embodiment, Comprising: (a), (b) is a figure which shows the state which the damper pin of a different diameter is contact | abutting to the platform. It is a figure explaining the 3rd modification of 1st embodiment, Comprising: (a), (b) is a figure explaining the damper pin of the combination of a different split pin. It is a figure explaining the 4th modification of a first embodiment, and (a) and (b) are figures explaining a damper pin from which the position of the direction of an axis of a coating layer differs. It is the figure which looked at the mutually adjacent platform of the gas turbine which concerns on 2nd embodiment from the axial direction. It is a perspective view of the moving blade group of the gas turbine which concerns on 3rd embodiment. It is XX sectional drawing of FIG.

<First embodiment>
Hereinafter, the gas turbine 1 which concerns on 1st embodiment of this invention is demonstrated with reference to FIGS. 1-3.

  As shown in FIG. 1, a 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 compressed air, and combustion. And a turbine 10 driven by gas.

  The compressor 2 includes a compressor rotor 3 that rotates about the axis O, and a compressor casing 4 that covers the compressor rotor 3 from the outer peripheral side. The compressor rotor 3 has a columnar shape extending along the axis O. On the outer peripheral surface of the compressor rotor 3, a plurality of compressor blade stages 5 arranged at intervals in the direction of the axis O are provided. Each compressor blade stage 5 has a plurality of compressor blades 6 arranged on the outer peripheral surface of the compressor rotor 3 at intervals in the circumferential direction of the axis O.

  The compressor casing 4 has a cylindrical shape centered on the axis O. A plurality of compressor vane stages 7 arranged at intervals in the direction of the axis O are provided on the inner peripheral surface of the compressor casing 4. These compressor vane stages 7 are alternately arranged with respect to the compressor blade stage 5 as viewed from the direction of the axis O. Each compressor vane stage 7 has a plurality of compressor vanes 8 arranged on the inner peripheral surface of the compressor casing 4 at intervals in the circumferential direction of the axis O.

  The combustor 9 is provided between the compressor casing 4 and a turbine casing 12 described later. The compressed air generated by the compressor 2 is mixed with fuel inside the combustor 9 to become a premixed gas. The premixed gas burns in the combustor 9 to generate high-temperature and high-pressure combustion gas. The combustion gas is guided into the turbine casing 12 to drive the turbine 10.

  The turbine 10 includes a turbine rotor 11 (rotary shaft) that rotates around an axis O, and a turbine casing 12 that covers the turbine rotor 11 from the outer peripheral side. The turbine rotor 11 has a columnar shape extending along the axis O. On the outer peripheral surface of the turbine rotor 11, a plurality of turbine blade stages 20 arranged at intervals in the direction of the axis O are provided. Each turbine blade stage 20 has a plurality of turbine blades 30 arranged on the outer peripheral surface of the turbine rotor 11 at intervals in the circumferential direction of the axis O. 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.

  The turbine casing 12 has a cylindrical shape centered on the axis O. A plurality of turbine vane stages 13 arranged at intervals in the direction of the axis O are provided on the inner peripheral surface of the turbine casing 12. These turbine stationary blade stages 13 are alternately arranged with respect to the turbine rotor blade stages 20 as viewed from the direction of the axis O. Each turbine stationary blade stage 13 has a plurality of turbine stationary blades 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. That is, the gas turbine rotor can be rotated integrally around the axis O in the gas turbine casing.

<Turbine blade>
Next, the turbine rotor blade 30 will be described in more detail with reference to FIG. A plurality of turbine rotor blades 30 are arranged in the circumferential direction on the outer peripheral side of the turbine rotor 11.
The turbine blade 30 includes a blade root 31, a platform 32, and a blade body 41.
The blade root 31 is a portion attached to the turbine rotor 11 in the turbine rotor blade 30. The turbine rotor 11 is configured by stacking a plurality of discs 11 a having a disk shape centering on the axis O in the direction of the axis O. The blade root 31 is integrally attached to the disk 11a by being fitted in a groove (not shown) of the disk 11a formed on the outer peripheral surface of the disk 11a from the direction of the axis O. Thereby, the turbine rotor blades 30 are arranged radially so as to be spaced apart from the disk 11a in the circumferential direction.

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

  The side surface 34 facing the circumferential direction in the platform 32 extends in the radial direction and in the axis O direction. The side surfaces 34 of the platforms 32 face each other in the circumferential direction between the platforms 32 of the turbine blades 30 adjacent to each other.

  A concave portion 37 that is recessed from the side surface 34 and extends in the direction of the axis O is formed on the side surface 34 of the platform 32. A damper accommodating space R1 extending so as to penetrate the platform 32 in the direction of the axis O according to the shape of the recesses 37 is defined by the recesses 37 of the adjacent platforms 32. The damper accommodating space R1 is formed between all adjacent platforms 32. Therefore, the same number of damper accommodating spaces R1 as the turbine rotor blades 30 are formed.

  The side surface 34 of each platform 32 is divided in the radial direction by the concave portion 37. Of the side surface 34 of the platform 32, the radially outer portion of the recess 37 is an outer peripheral side surface 35, and the radially inner portion of the recess 37 is an inner peripheral side surface 36.

  As shown in FIGS. 2 and 3, the surface facing the radially inner side of the recess 37 of the platform 32 is a damper contact surface 38. The damper contact surface 38 has a planar shape parallel to the axis O. The damper abutting surface 38 is inclined and extended toward the outer side in the circumferential direction toward the outer side in the radial direction of each turbine blade 30, and is connected to the outer peripheral side surface 35 of the platform 32. The damper contact surfaces 38 of the platforms 32 adjacent to each other face each other in the circumferential direction. These damper contact surfaces 38 are inclined so that the facing distance becomes shorter toward the outer side in the radial direction. Note that only one of the pair of damper contact surfaces 38 may be inclined and the other may be configured along the radial direction.

  As shown in FIG. 1, the end of the damper contact surface 38 opposite to the outer peripheral side surface 35 is connected to the radially outer end of a concave bottom surface 39 that extends parallel to the axis O and extends in the radial direction. . A recess lower surface 40 that is parallel to the axis O and extends in the circumferential direction is formed between the radially inner end of the recess bottom surface 39 and the radially outer end of the inner peripheral side surface 36. The damper accommodating space R <b> 1 is defined by a damper contact surface 38, a concave bottom surface 39, and a concave bottom surface 40 between the platforms 32 adjacent to each other.

  The wing body 41 extends radially outward from the outer peripheral surface 33 of the platform 32. That is, the base end of the blade body 41 is integrally connected to the radially outer end of the platform 32. The wing body 41 has a wing shape in cross section perpendicular to the extending direction of the wing body 41.

<Damper pin>
As shown in FIGS. 2 and 3, a damper pin 50 (damper member) is accommodated in each damper accommodating space R1. That is, the same number of damper pins 50 as the damper accommodating spaces R1 are provided corresponding to the damper accommodating spaces R1. The damper pin 50 is a member having a pin shape extending in the axis O direction. The damper pin 50 has a circular cross-sectional view perpendicular to the axis O, and extends in the direction of the axis O with a uniform outer diameter. The outer diameter of the damper pin 50 is set larger than the interval between the outer peripheral side surfaces 35 of the adjacent platforms 32. The outer shapes of the damper pins 50 are the same.

The damper pin 50 of the present embodiment has a damper pin main body 51 (damper member main body) and a coating layer 52.
The damper pin main body 51 is a portion that becomes a base portion of the damper pin 50 and has a pin shape extending in the axis O direction. The damper pin main body 51 has a circular shape in which the cross-sectional shape orthogonal to the axis O is slightly smaller than the cross-sectional shape of the damper pin 50. The damper pin main body 51 has a uniform outer diameter and extends in the direction of the axis O. The damper pin main body 51 is made of a metal such as steel. The outer shape of the damper pin body 51 of each damper pin 50 is the same.

  The coating layer 52 is a member that covers the outer peripheral surface of the damper pin main body 51. The coating layer 52 is laminated on the outer peripheral surface of the damper pin main body 51 with a uniform thickness. The coating layer 52 is made of a material such as diamond-like carbon (DLC) or tungsten carbide, for example. The outer peripheral surface of the coating layer 52 is exposed to the outside as the outer peripheral surface of the damper pin 50. The outer shape of the coating layer 52 of each damper pin 50 is the same.

  In this embodiment, as shown in FIG. 3, the damper pin 50A and the damper pin 50B have different structures.

  More specifically, the coating layer 52A of the damper pin 50A is formed from diamond-like carbon as the first material. Further, the coating layer 52B of the damper pin 50B is formed of tungsten carbide as the second material. Diamond-like carbon and tungsten carbide have different friction coefficients. The friction coefficient of diamond-like carbon is smaller than that of tungsten carbide. Therefore, in this embodiment, the friction coefficient of the outer peripheral surface of the damper pin 50A is smaller than the friction coefficient of the outer peripheral surface of the other damper pin 50B.

<Effect>
During the rotation of the turbine 10, a centrifugal force directed radially outward acts on each damper pin 50. As a result, as shown in FIG. 3, the outer peripheral surface of the damper pin 50 contacts both of the damper contact surfaces 38 of the platforms 32 while closing the gap between the outer peripheral side surfaces 35 of the adjacent platforms 32. At this time, when an excitation force acts on the blades of the turbine 10, the damper pin 50 slides with respect to the damper contact surface 38, thereby generating friction between the damper pin 50 and the damper contact surface 38. Thereby, attenuation of the vibration by the frictional force can be obtained.

  Here, for example, when all the damper pins 50 have the same structure, the timing at which each damper pin 50 starts to slide with respect to the damper contact surface 38 is the same. That is, when a certain excitation force is applied, a frictional force is generated between all the damper contact surfaces 38 and the damper pins 50. Thus, although an appropriate attenuation can be given to a specific excitation force, only the excitation force within a very limited range can exhibit the attenuation.

  On the other hand, in this embodiment, two types of damper pins 50A and 50B having different friction coefficients on the outer peripheral surface are provided. Therefore, the timing when these two types of damper pins 50A and 50B start to slide is different. The damper pin 50 </ b> A having the diamond-like carbon coating layer 52 </ b> A having a relatively small friction coefficient slides when a relatively small excitation force is applied, thereby imparting damping due to friction. On the other hand, the damper pin 50B having the tungsten carbide coating layer 52B having a relatively large friction coefficient slips when a relatively large excitation force is applied, thereby imparting damping due to friction. As a result, vibration can be effectively suppressed over a wide range of excitation forces.

  Further, the turbine 10 blade as a whole can have a mistuned structure because the damper pin 50 slides differently from the damper contact surface 38 of the turbine rotor blade 30. Thereby, the flutter resistance can be improved.

Further, since the excitation force at which the damper pin 50 slides between the turbine 10 blades differs, even if the excitation force and the vibration level change, the change in the frequency of the turbine blade stage 20 as a whole can be reduced.
On the other hand, at a stage where the excitation force is small and the damper pins 50 are not slid out, the influence of the difference in the friction coefficient of the outer peripheral surface of each damper pin 50 on the frequency of the turbine blade 30 as a whole is small. Therefore, when the excitation force is relatively small, the vibration characteristics can be easily predicted.

  Furthermore, in this embodiment, the friction coefficient of the outer peripheral surface of the damper pin 50 can be changed inexpensively and easily by changing the material of the coating layer 52.

  In the present embodiment, the friction coefficient of the outer peripheral surface of the damper pin 50 is changed by changing the material of the coating layer 52, but the present invention is not limited to this. For example, the friction coefficient may be changed by changing the surface roughness of the coating layer 52. Further, the friction coefficient may be changed by changing the surface roughness of the surface of the damper pin main body 51 without providing the coating layer 52. The surface roughness can be easily changed by machining or chemical treatment.

  In the first embodiment, the example using the coating layers 52A and 52B of two materials has been described. However, three or more types of damper pins 50 may be configured using three or more types of coating layers. That is, you may comprise the several damper pin 50 from which a friction characteristic differs mutually.

  The structure of the damper pin 50 may be different so that the friction characteristic of at least one damper pin 50 is different from the friction characteristic of other damper pins 50. Further, it is only necessary that the pressing load of at least one damper pin 50 on the damper contact surface 38 differs from the pressing load of the other damper pins 50 on the damper contact surface 38 when the turbine 10 rotates. As a result, the friction characteristics can be made different between the damper pins 50. That is, the plurality of damper pins 50 do not have the same structure, but at least one of the plurality of damper pins 50 only needs to have a different structure from the other damper pins 50. As a result, a mistune structure can be obtained, and flutter resistance can be improved.

Furthermore, the friction coefficient of the damper contact surface 38 with which at least one of the plurality of damper pins 50 contacts may be different from the friction coefficient of the damper contact surface 38 with which another damper pin 50 contacts.
Further, for example, the above configuration may be realized by forming a coating layer on the surface of the damper contact surface 38 and changing the material of the coating layer for each damper contact surface 38. Further, the above configuration may be realized by changing the surface roughness of the damper contact surface 38.

<First Modification of First Embodiment>
Here, as a first modification of the first embodiment, for example, as shown in FIG. 4, each of the damper pins 60A and 60B is formed only from the damper pin bodies 61A and 61B, and the mother is a material for forming the damper pin bodies 61A and 61B. The material may be different between the damper pins 60A and 60B. That is, the base material of the damper pin 61A may be formed from the first material, and the base material of the damper pin 61B may be formed from the second material.

  When the material of the base material of the damper pins 60A and 60B (damper pin main bodies 61A and 61B) is different, the density of the damper pins 60A and 60B is different. For this reason, the weights of the damper pins 60A and 60B as a whole are also different. Thereby, the pressing load from the damper pins 60A and 60B to the damper contact surface 38 of the platform 32 when the centrifugal force is applied to the damper pins 60A and 60B can be changed. If the pressing load differs for each of the damper pins 60A and 60B, the frictional force between the damper pins 60A and 60B and the damper contact surface 38 also changes. Accordingly, as in the first embodiment, attenuation can be applied to a wide range of excitation forces.

  Further, since the base material of the damper pins 60A and 60B is exposed on the surface, a frictional force based on the friction coefficient for each material of the base material is generated. This also makes it possible to generate different frictional forces for each of the damper pins 60A and 60B.

<Second Modification of First Embodiment>
As a second modification of the first embodiment, for example, as shown in FIG. 5, the diameters of the outer peripheral surfaces of the plurality of damper pins 70A and 70B may be different from each other. The diameter of the damper pin 70A may be relatively small, and the diameter of the damper pin 70B may be relatively large.

  Since the diameters of the damper pins 70A and 70B are different, the weights of the damper pins 70A and 70B are different, and the contact positions of the damper pins 70A and 70B on the damper contact surface 38 are different for each platform 32. As a result, by changing the timing at which the damper pins 70A and 70B start to slide, attenuation can be applied to a wide range of excitation forces.

<Third Modification of First Embodiment>
As a third modification of the first embodiment, for example, as shown in FIG. 6, the damper pins 80A and 80B may be composed of a plurality of divided pins 81a, 81b, 81c and 81d. That is, in the third modification, the damper pins 80A and 80B have a configuration in which a plurality of divided pins 81a, 81b, 81c, and 81d are joined in the axis O direction. The plurality of split pins 81a, 81b, 81c, 81d have various structures having different materials, sizes, and shapes. As shown in FIGS. 6A and 6B as an example, the plurality of damper pins 80A and 80B are configured by combinations of different divided pins 81a, 81b, 81c, and 81d. Accordingly, the weights and densities of the plurality of damper pins 80A and 80B can be made different from each other. Therefore, as in the first embodiment, a wide range of excitation forces can be handled.

<Fourth Modification of First Embodiment>
As a fourth modification of the first embodiment, for example, a configuration shown in FIG. 7 may be used. That is, in the damper pins 90A and 90B of the fourth modified example, the coating layers 92A and 92B are formed only in a part of the outer peripheral surface of the damper pin main body 91 in the axis O direction. Then, as shown in FIGS. 7A and 7B, the position of the coating layer 92A of at least one damper pin 90A among the plurality of damper pins 90A and 90B in the direction of the axis O is the coating layer 92B of the other damper pin 90B. Is different from the position in the direction of the axis O.

Here, the amplitude of the damper pins 90A and 90B at the time of excitation may not be uniform in the direction of the axis O depending on the vibration mode shape. For this reason, wear at the position in the axis O direction where the amplitude of the damper pins 90A and 90B is large becomes large. In this modification, wear of the damper pins 90A and 90B can be suppressed by forming the coating layers 92A and 92B only at the position in the direction of the axis O where the amplitude increases in this way.
In addition, by changing the position of the coating layer 92A, 92B in the axis O direction for each of the damper pins 90A, 90B, the vibration characteristics for each of the damper pins 90A, 90B can be changed, and a wide range of excitation forces can be handled. It becomes.

<Second embodiment>
Next, a second embodiment will be described with reference to FIG. The same components as those in the first embodiment are denoted by the same reference numerals, and detailed description thereof is omitted.
In the second embodiment, a groove portion 100 extending from the side surface 34 in the direction of the recessed axis O is formed on the side surface 34 of the platform 32 of the turbine rotor blade 30. And the leaf | plate spring accommodation space R2 extended so that the platform 32 may penetrate in the axis line O direction according to the shape of these groove parts 100 is formed by the groove parts 100 of the adjacent platform 32. FIG.

  The side surface 34 of each platform 32 is divided in the radial direction by the groove 100. Of the side surface 34 of the platform 32, the radially outer portion of the groove portion 100 is an outer peripheral side surface 35, and the radially inner portion of the groove portion 100 is an inner peripheral side surface 36.

  The surface facing the radially inner side in the groove portion 100 of the platform 32 is a groove portion upper surface 101. The groove upper surface 101 is connected to the lower end of the outer peripheral side surface 35. The end of the groove upper surface 101 opposite to the outer peripheral side surface 35 is connected to the radially outer end of the groove bottom surface 102 that extends parallel to the axis O and extends in the radial direction. Between the radially inner end of the groove bottom surface 102 and the radially outer end of the inner peripheral side surface 36 is formed a groove lower surface 103 that extends in the circumferential direction parallel to the axis O and faces radially outward. ing. The leaf spring accommodating space R <b> 2 is defined by a groove upper surface 101, a groove lower surface 102, and a groove lower surface 103 between adjacent platforms 32.

<Leaf spring damper>
In the present embodiment, the leaf spring damper 110 (damper member) is accommodated in the leaf spring accommodating space R2. The leaf spring damper 110 has a C-shaped cross section orthogonal to the axis O that opens radially outward. The leaf spring damper 110 has a uniform cross-sectional shape and extends in the direction of the axis O.

  The leaf spring damper 110 is in surface contact with the groove portion upper surface 101 of the groove portion 100 at both ends of the C-shaped cross section. The opening in the C-shaped cross section of the leaf spring damper 110 is located between the pair of outer peripheral side surfaces 35. In addition, the leaf spring damper 110 is in contact with the groove bottom surface 102 and the groove bottom surface 103 sequentially at the inner side of both ends of the C-shaped cross section. A portion between the pair of groove lower surfaces 103 in the leaf spring damper 110 extends over these groove lower surfaces 103. The leaf spring damper 110 is biased in a direction to open an opening having a C-shaped cross section.

The leaf spring damper 110 has a leaf spring damper main body 111 and a coating layer 112.
The leaf spring damper main body 111 is made of metal and constitutes an inner portion of the leaf spring damper 110 having a C-shaped cross section. The coating layer 112 constitutes an outer portion of the leaf spring damper 110 having a C-shaped cross section, and is laminated on the outer surface of the leaf spring damper 110 (the surface facing the outer side of the sectional C shape). The coating layer 112 is in contact with the groove part upper surface 101, the groove part bottom surface 102, and the groove part lower surface 103 of the groove part 100. A plurality of such leaf spring dampers 110 are provided corresponding to each leaf spring accommodating space R2.

  Here, in the present embodiment, the coating layer 112 of some of the leaf spring dampers 110 among the plurality of leaf spring dampers 110 is formed of diamond-like carbon as the first material. Further, the coating layer 112 of other leaf spring dampers 110 excluding a part of the leaf spring dampers 110 among the plurality of leaf spring dampers 110 is formed of tungsten carbide as the second material. Therefore, the friction coefficient of the outer surface of some leaf spring dampers 110 is smaller than the friction coefficient of the outer surfaces of other leaf spring dampers 110.

<Effect>
The leaf spring damper 110 presses the inner surface of the groove portion 100 of the adjacent platform 32 with an urging force. When an excitation force acts on the turbine, the outer surface of the leaf spring damper 110 slides with respect to the inner surface of the groove portion 100, and a frictional force is generated between the leaf spring damper 110 and the inner surface of the groove portion 100. Thereby, attenuation of the vibration by the frictional force can be obtained.

  On the other hand, in this embodiment, two types of leaf spring dampers 110 having different outer peripheral friction coefficients are provided. Therefore, the timings at which these two types of leaf spring dampers 110 begin to slide are different. Therefore, as in the first embodiment, vibration can be effectively suppressed over a wide range of excitation force.

  In the second embodiment, the structure of the leaf spring damper 110 only needs to be different so that the friction characteristic of at least one leaf spring damper 110 is different from the friction characteristic of other leaf spring dampers 110.

Further, the friction coefficient of the inner surface of the groove portion 100 with which at least one of the plurality of leaf spring dampers 110 abuts may be different from the friction coefficient of the inner surface of the groove portion 100 with which the other leaf spring damper 110 abuts. For example, it may be realized by forming a coating layer on the inner surface of the groove 100 and changing the material of the coating layer between the grooves 100. Moreover, you may implement | achieve by changing the surface roughness of the inner surface of the groove part 100. FIG.
Further, three or more types of leaf spring dampers 110 may be applied using three or more types of coating layers.

The leaf spring damper 110 may be configured only from the leaf spring damper main body 111, and the material constituting the leaf spring damper main body 111 may be different between the leaf spring dampers 110.
The size of the leaf spring damper 110 may be different between the leaf spring dampers 110.
The coating layer 112 may be formed only in a partial region of the leaf spring damper main body 111 in the axis O direction. In this case, the positions in the axis O direction of the coating layer 112 between the leaf spring dampers 110 may be different.
The leaf spring damper 110 may be configured by combining a plurality of leaf spring damper pieces. In this case, you may comprise these leaf | plate spring dampers 110 from the combination of the leaf | plate spring damper piece which differs between leaf | plate spring dampers 110. FIG.

<Third embodiment>
Next, a third embodiment will be described with reference to FIGS. In the third embodiment, the same components as those in the first and second embodiments are denoted by the same reference numerals, and detailed description thereof is omitted.
The turbine rotor blade 30 of the third embodiment has a shroud 120 at the radially outer end of the blade body 41. The shroud 120 is provided so as to protrude from the tip of the blade body 41 in the direction of the axis O and the circumferential direction. A part of the side surface 121 facing the circumferential direction in the shroud 120 is a contact surface 130 that abuts the shrouds 120 adjacent to each other in the circumferential direction when the turbine 10 rotates.

  In the present embodiment, as shown in FIG. 10, a coating layer 140 is formed on a part of the side surface 121 of the shroud 120. The surface of the coating layer 140 is a contact surface 130 that contacts the adjacent shrouds 120. A friction damper 150 is constituted by contact surfaces 130 of adjacent shrouds 120. In the present embodiment, the friction damper 150 is configured at the contact point of each contact surface 130, that is, a plurality of friction dampers 150 are configured.

  Here, in the present embodiment, the material of the coating layer 140 of the contact surface 130 that constitutes a part of the friction dampers 150 among the plurality of friction dampers 150 constitutes the other friction dampers 150 excluding the part of the friction dampers 150. It differs from the material of the coating layer 140 of the contact surface 130 to be made. Specifically, the coating layer 140 of some friction dampers 150 is made of a first material, and the coating layers 140 of other friction dampers 150 are made of a second material. The first material and the second material are materials having different friction coefficients. For example, as in the first embodiment, diamond-like carbon can be used as the first material, and tungsten carbide can be used as the second material.

<Effect>
In the present embodiment, the friction coefficients of the coating layers 140 that constitute some of the friction dampers 150 and other friction dampers 150 are different. Therefore, the friction characteristics in each friction damper 150 are different. Therefore, like the first and second embodiments, these friction dampers 150 can give vibration damping to a wide range of excitation forces. Therefore, the flutter resistance can be improved.

Note that three or more types of friction dampers 150 may be configured using three or more types of coating layers 140.
For example, as a modification of the third embodiment, the friction characteristics of each friction damper 150 may be changed by making the contact area of the contact surface 130 of the friction damper 150 different for each friction damper 150. In this case as well, vibration damping can be applied to a wide range of excitation forces as described above.
Further, the friction damper 150 may be configured by using the side surface of the shroud 120 as the contact surface 130 and directly contacting these side surfaces without using the coating layer 140. At this time, the friction characteristics may be changed by changing the surface roughness of the side surface of the shroud 120 for each friction damper 150.

<Other embodiments>
The embodiment of the present invention has been described above, but the present invention is not limited to this, and can be appropriately changed without departing from the technical idea of the present invention.
For example, in the embodiment, an example in which the present invention is applied to the turbine rotor blade 30 of the gas turbine 1 has been described. However, the present invention is applied to a rotor blade of another rotating machine such as a rotor blade of a jet engine or a rotor blade of a steam turbine. You may apply.

DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Compressor 3 Compressor rotor 4 Compressor casing 5 Compressor blade stage 6 Compressor blade 7 Compressor stationary blade stage 8 Compressor stationary blade 9 Combustor 10 Turbine 11 Turbine rotor (rotary shaft)
11a Disc 12 Turbine casing 13 Turbine stator blade stage 14 Turbine stator blade 20 Turbine rotor blade stage 30 Turbine rotor blade 31 Blade root 32 Platform 33 Outer peripheral surface 34 Side surface 35 Outer peripheral side surface 36 Inner peripheral side surface 37 Recess 38 Damper contact surface 39 Recess bottom surface 40 Recess bottom surface 41 Wing body 50 Damper pin (damper member)
50A damper pin 50B damper pin 51 damper pin body 52 coating layer 52A coating layer 52B coating layer 60A damper pin 60B damper pin 61A damper pin body 61B damper pin body 70A damper pin 70B damper pin 80A damper pin 80B damper pin 81a partition pin 81b partition pin 81c partition pin 81c partition pin 81c partition pin 81c partition pin 81c partition pin 81c 91 damper pin main body 92A coating layer 92B coating layer 100 groove part 101 groove part upper surface 102 groove part bottom surface 103 groove part lower surface 110 leaf spring damper (damper member)
111 Leaf spring damper main body 112 Coating layer 120 Shroud 121 Side 130 Contact surface 140 Coating layer 150 Friction damper R1 Damper accommodating space R2 Leaf spring accommodating space O Axis line

Claims (13)

A rotation axis that rotates about an axis,
A plurality of rotor blades arranged circumferentially on the outer peripheral side of the rotating shaft, the blade root attached to the rotating shaft, a platform provided radially outside the blade root, and a radially outer side from the platform A rotor blade having a blade body extending to
A plurality of damper members which are respectively provided between the blades adjacent to each other, and whose surfaces are in contact with both platforms of the adjacent blades;
With
A rotating machine in which at least one of the plurality of damper members has a different structure from the other damper members.   The rotating machine according to claim 1, wherein a friction coefficient of a surface of at least one of the plurality of damper members is different from a friction coefficient of a surface of the other damper member. The damper member is
A damper member body;
A coating layer covering the outer surface of the damper member main body,
The rotating machine according to claim 1 or 2, wherein a material of the coating layer of at least one of the plurality of damper members is different from a material of the coating layer of the other damper members.   The rotating machine according to any one of claims 1 to 3, wherein a weight of at least one of the plurality of damper members is different from a weight of the other damper members. The damper member has a damper member body formed from a base material,
The material of the base material of the damper member main body of at least one of the plurality of damper members is different from the material of the base material of the damper member main body of the other damper member. The rotating machine described. The damper member has a pin shape extending in the axial direction,
6. The rotating machine according to claim 1, wherein an outer diameter of at least one of the plurality of damper members is different from an outer diameter of the other damper member. The damper member has a pin shape extending in the axial direction and includes a plurality of divided pins connected in the axial direction.
The plurality of split pins have different configurations from each other,
The rotating machine according to any one of claims 1 to 6, wherein at least one of the plurality of damper members includes a combination of the split pins different from the other damper members. The damper member is
A damper body extending in the axial direction;
A coating layer that covers only a part of the outer peripheral surface of the damper main body in the axial direction;
The position in the axial direction of the coating layer of at least one of the damper members among the plurality of damper members is different from the position in the axial direction of the coating layer of another damper member. A rotating machine according to claim 1. A rotation axis that rotates about an axis,
A plurality of rotor blades arranged circumferentially on the outer peripheral side of the rotating shaft, the blade root attached to the rotating shaft, a platform provided radially outside the blade root, and a radially outer side from the platform A rotor blade having a blade body extending to
A plurality of damper members provided between the blades adjacent to each other, the surfaces of which are in contact with both of the damper contact surfaces of the platforms of the adjacent blades;
With
A rotary machine in which a friction coefficient of the damper contact surface with which at least one of the plurality of damper members contacts is different from a friction coefficient of the damper contact surface with which the other damper member contacts. The damper contact surface is formed by a coating layer laminated on the surface of the platform,
The friction coefficient of the coating layer on the damper contact surface with which at least one of the plurality of damper members contacts is different from the friction coefficient of the coating layer on the damper contact surface with which the other damper member contacts. Item 10. The rotating machine according to Item 9. A part of the damper contact surface is formed by a coating layer laminated on the surface of the platform,
The axial position of the coating layer on the damper contact surface with which at least one of the damper members contacts is the axis of the coating layer on the damper contact surface with which the other damper member contacts. The rotating machine according to claim 9 or 10, which is different from the directional position. A rotation axis that rotates about an axis,
A plurality of rotor blades arranged circumferentially on the outer peripheral side of the rotary shaft, the blade root attached to the rotary shaft, a blade body extending radially outward from the blade root, and a radially outer side of the blade body A rotor blade having a shroud provided at the end of
With
The shroud is
Having a contact surface constituting a friction damper by abutting each other between the adjacent shrouds;
A rotary machine configured such that a friction force generated in at least one of the plurality of friction dampers is different from a friction force in the other friction dampers. The contact surface is formed by a coating layer laminated on the surface of the shroud,
The rotating machine according to claim 12, wherein a friction coefficient of the coating layer of at least one of the friction dampers is different from a friction coefficient of the coating layer of the other friction damper.

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