JP2019173659A - Rotary machine - Google Patents

Abstract

To provide a rotary machine capable of attaining an effective vibration attenuation effect while improving durability against abrasion.SOLUTION: This invention comprises a revolving shaft rotated around an axial line, several moving blades arranged at an outer peripheral side of the revolving shaft in a peripheral direction, a blade root attached to the revolving shaft, a platform arranged outside of said blade root in a radial direction, a moving blade having a blade main body extending from said platform to outside in a radial direction, several dumper pins 50 each of which is arranged between the moving blades adjacent to each other and several dumper pins 50 of which surfaces abut against both platforms of the moving blades. The damper pins comprise a dumper pin main body 51 and a coating layer 52 covering the surface of the dumper pin main body 51 and at the same time formed by material with lower friction coefficient than that of the dumper pin main body 51.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, the damping force of the damper is determined by the relationship between the frictional force acting between the turbine blade and the excitation force generated on the turbine blade. It is necessary to design a damper that can correctly predict the excitation force and apply an appropriate excitation force.
On the other hand, the damper and the turbine rotor blade are gradually worn over time by contacting each other. In particular, when the excitation force is larger than expected, the wear of the damper proceeds more than expected and an appropriate damping effect cannot be obtained. In such a case, it is necessary to replace the damper with a new one, and the maintenance frequency increases.

  This invention is made | formed in view of such a situation, Comprising: It aims at providing the rotary machine which can acquire an effective vibration damping effect, improving durability with respect to abrasion.

The present invention employs the following means in order to solve the above problems.
That is, the rotating machine according to the first aspect of the present invention includes a rotating shaft that rotates around an axis, and a plurality of moving blades arranged in the circumferential direction on the outer peripheral side of the rotating shaft, and is attached to the rotating shaft. A blade having a blade root, a platform provided on the radially outer side of the blade root, and a blade body extending radially outward from the platform, and adjacent to each other between the blades adjacent to each other. A plurality of damper members whose surfaces abut against both platforms of the rotor blades, the damper member covering the surface of the damper member main body and the damper member main body and having a friction coefficient higher than that of the damper member main body. A coating layer formed from a small material.

Usually, the coating layer on the surface of the damper member is selected so as to give appropriate attenuation to the predicted excitation force. Here, when the excitation force is larger than expected, since the frictional damping generated by the slip between the damper member and the platform is too small with respect to the excitation force, the damping effect cannot be obtained appropriately. Moreover, since the amplitude is larger than expected, the wear of the coating layer proceeds.
In this aspect, when the wear of the coating layer proceeds, the surface of the damper member having a friction coefficient larger than that of the coating layer is exposed. By generating a frictional force between the surface of the damper member and the platform, it is possible to give an appropriate frictional damping to an excitation force that is greater than expected. Thereby, it becomes possible to continue using the damper member until the next maintenance time.

  In the rotary machine of the above aspect, the damper member main body extends in the axial direction, and the coating layer may be formed only in a partial region in the axial direction on the outer peripheral surface of the damper member main body. Good.

  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, wear of the damper member can be suppressed by providing the coating layer only in the axial direction position where the amplitude becomes large in this way.

  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 moving blade having a platform provided radially outward of the blade root and a blade body extending radially outward from the platform, and formed on a surface of the platform and having a smaller coefficient of friction than the surface of the platform A coating layer; and a plurality of damper members provided between the blades adjacent to each other and having a surface abutting against both of the coating layers on the platforms of the adjacent blades.

According to the rotating machine, when the excitation force is larger than expected, the wear of the coating layer proceeds more than expected due to the friction generated by the slip between the damper member and the coating layer on the platform.
When the coating layer is worn in this way, the surface of the platform having a higher coefficient of friction than the coating layer is exposed. Then, by generating a frictional force between the surface of the platform and the damper member, it is possible to give an appropriate frictional damping to an excitation force that is greater than expected. As a result, the platform can be used without any repair until the next maintenance time.

  In the rotating machine, the damper member main body has a pin shape extending in the axial direction, and the platform has a damper contact surface in which the opposing distance in the circumferential direction becomes smaller toward the radially outer side between adjacent platforms. The coating layer is formed on the surface of the damper contact surface, and the friction coefficient of the coating layer increases as the facing distance between the coating layers facing in the circumferential direction increases. Also good.

  As the excitation force increases, the amplitude also increases, so that the damper member comes into contact with a wide range of the damper contact surface. By setting the friction coefficient of the coating layer so as to increase according to the facing distance between the coating layers, a large frictional force corresponding to the vibration amplitude can be generated between the damper member and the damper contact surface. As a result, the vibration amplitude can be suppressed.

  In the rotating machine of the above aspect, the damper member main body extends in the axial direction, the platform has a damper contact surface, and the coating layer is the axis of the damper contact surface of the platform. It may be formed only in a partial region in the direction.

  When wear of only a part of the platform in the axial direction on the damper contact surface is likely to proceed, it is effective to form a coating layer on only a part of the axis of the damper contact surface in the axial direction. Abrasion can be suppressed.

  A rotating machine according to an aspect of the present invention includes a rotating shaft that rotates around an axis and a plurality of moving blades arranged in a circumferential direction on an 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 a radially outer end of the blade body, the shrouds abutting each other between adjacent shrouds. And a contact surface that constitutes a friction damper, and the contact surface is formed by a coating layer that is laminated on the surface of the shroud and has a smaller friction coefficient than the surface of the shroud.

According to the rotating machine, when the excitation force is larger than expected, the wear of the coating layer forming the contact surface proceeds more than expected due to the friction generated by the slip between the contact surfaces.
When the coating layer is worn in this way, the surface of the shroud having a friction coefficient larger than that of the coating layer is exposed. And since the surface of such a shroud contacts and functions as a friction damper, appropriate friction damping can be given with respect to the excitation force beyond assumption. This allows the shroud to continue to be used without repair until the next maintenance time.

  In the rotating machine of the above aspect, the coating layer may be formed in a plurality of layers, and each of the coating layers may have a smaller friction coefficient as the coating layer on the surface side.

  As a result, when an excitation force more than expected is generated, the coating layer is sequentially worn from the surface, and the coefficient of friction gradually increases. When the coating layer having a friction coefficient corresponding to the excitation force is exposed, appropriate attenuation can be applied to the excitation force that is greater than expected.

  According to the rotating machine of the present invention, it is possible to obtain an effective vibration damping effect while improving durability against wear.

It is a typical longitudinal section of the gas turbine concerning a first embodiment. It is the typical figure which looked at the turbine rotor blade stage of the gas turbine concerning a first embodiment from the direction of an axis. It is the principal part enlarged view of FIG. 2, Comprising: It is the figure which looked at the platform which mutually adjoins the gas turbine which concerns on 1st embodiment from the axial direction. It is a typical side view of the damper pin concerning the modification of a first embodiment. 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 the figure which looked at the mutually adjacent platform of the gas turbine which concerns on 3rd embodiment from the axial direction. It is the figure which looked at the mutually adjacent platform of the gas turbine which concerns on 4th embodiment from the axial direction. It is a perspective view of the moving blade group of the gas turbine which concerns on 5th embodiment. It is IX-IX 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 that rotates about 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 on the inner peripheral surface of the turbine casing 12 at intervals in the circumferential direction of the axis OO. 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.
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.

  As shown in FIG. 3, the side surface 34 facing the circumferential direction of 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.

  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.

Here, in this embodiment, the friction coefficient of the surface of the damper pin main body 51 is larger than the friction coefficient of the material forming the coating layer 52. That is, the material of the coating layer 52 that covers the damper pin main body 51 has a smaller coefficient of friction than the surface of the damper pin main body 51.
The damper pin main body 51 is made of, for example, a material having a friction coefficient larger than that of the material forming the coating layer 52. Thereby, the friction coefficient of the surface of the damper pin main body 51 is larger than the friction coefficient of the coating layer 52. In addition, the friction coefficient of the damper pin main body 51 may be set to be larger than the friction coefficient of the coating layer 52 by roughening the surface of the damper pin main body 51 by, for example, machining or chemical processing.

<Effect>
When the turbine 10 rotates, a centrifugal force acting 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 turbine rotor blade 30, the damper pin 50 slides with respect to the damper contact surface 38, and friction is generated between the damper pin 50 and the damper contact surface 38. Thereby, the damping effect of the vibration by the friction force can be obtained.

In general, the coating layer 52 on the surface of the damper pin 50 is designed so that appropriate damping can be given to the predicted excitation force. As a result, vibration can be effectively reduced.
Here, since the excitation force of the turbine 10 is determined by various factors, it is difficult to predict accurately. Therefore, in some cases, the actually applied excitation force may greatly exceed the predicted excitation force. When the excitation force is larger than expected, the damping effect generated by the slip between the damper pin 50 and the damper abutting surface 38 is too small with respect to the excitation force, so that the damping effect cannot be obtained appropriately. Further, since the amplitude is larger than expected, the wear of the coating layer 52 proceeds more than expected.

  In this embodiment, when the wear of the coating layer 52 proceeds, the surface of the damper pin main body 51 having a larger coefficient of friction than the coating layer 52 is exposed. The frictional force between the surface of the damper pin main body 51 and the damper contact surface 38 is larger than the frictional force between the coating layer 52 and the damper contact surface 38 having a relatively small friction coefficient. In other words, the surface of the damper pin main body 51 is exposed, and frictional damping can be effectively applied to an exciting force exceeding expectation. Thereby, it can suppress that abrasion of the damper pin 50 further advances, exhibiting a damping effect. Therefore, the damper pin 50 can continue to be used until the next maintenance time. That is, according to the present embodiment, an effective vibration damping effect can be obtained while improving durability against wear.

  Here, in the damper pin 50, for example, a plurality of coating layers 52 may be formed. In this case, the coating layer 52 made of different materials is sequentially formed on the surface of the damper pin main body 51. Further, the coating layer on the surface side of the damper pin 50 is made of a material having a smaller friction coefficient. For example, when the coating layer 52 is formed of two layers, the inner coating layer 52, that is, the coating layer 52 laminated on the surface of the damper pin main body 51 is formed of tungsten carbide having a relatively high friction coefficient. On the other hand, the outer layer, that is, the layer forming the surface of the damper pin 50 is formed of diamond-like carbon having a relatively small friction coefficient.

  As a result, when an excitation force more than expected is generated, the coating layer 52 is sequentially worn from the surface side, and the friction coefficient gradually increases. Then, at the stage where the surface of the coating layer 52 or the damper pin main body 51 having a friction coefficient corresponding to the excitation force is exposed, appropriate attenuation can be imparted to the excitation force that is greater than expected.

  In the first embodiment, the example in which the damper pin 50 is configured by forming the coating layer 52 over the entire region of the damper pin main body 51 in the axis O direction has been described. However, the present invention is not limited to this. For example, as in the modification shown in FIG. 4, the coating layer 52 is formed only in a partial region of the damper pin main body 51 in the axis O direction, and the axis O of the damper pin main body 51 is formed. It is good also as a structure which exposed the outer peripheral surface of the damper pin main body 51 in the other area | region of a direction.

  Here, the amplitude of the damper pin 50 may not be uniform in the direction of the axis O depending on the vibration mode shape. As a result, wear at the position in the axis O direction where the amplitude of the damper pin 50 is large becomes large. In the above configuration, wear of the damper pin 50 can be suppressed by providing the coating layer only at the position in the direction of the axis O where the amplitude increases in this way.

<Second embodiment>
Next, a second embodiment of the present invention will be described with reference to FIG. In the second embodiment, 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, the damper pin 50 does not have the coating layer 52 of the first embodiment, and is formed only from the damper pin main body 51. On the other hand, a plurality of coating layers 60 </ b> A and 60 </ b> B are formed on the damper contact surface 38 of the platform 32.

  The coating layers 60A and 60B are formed over the entire area of both the damper contact surfaces 38 of the platforms 32 adjacent to each other. In the present embodiment, two coating layers 60A and 60B are formed. The inner coating layer 60A is a layer directly formed on the damper contact surface 38, and is formed with a uniform thickness. The outer coating layer 60B is a layer further laminated on the inner coating layer 60A, and is formed with a uniform thickness.

In the present embodiment, the inner coating layer 60A is formed of a material having a relatively large friction coefficient. The inner coating layer 60A is made of, for example, tungsten carbide. The friction coefficient of the inner coating layer 60 </ b> A is smaller than the friction coefficient of the damper contact surface 38.
The outer coating layer 60B is made of a material having a relatively small friction coefficient. The outer coating layer 60B is made of, for example, diamond-like carbon.

<Effect>
According to the second embodiment, when the excitation force is larger than expected, the friction generated by the sliding between the damper pin 50 and the outer coating layer 60B laminated on the damper contact surface 38 of the platform 32, Wear of the outer coating layer 60B proceeds more than expected.
When the outer coating layer 60B is worn in this way, the inner coating layer 60A having a higher friction coefficient than the outer coating layer 60B is exposed. Then, a frictional force is generated between the surface of the inner coating layer 60 </ b> A and the damper pin 50. When the friction force is suitable for the applied excitation force, an appropriate damping effect can be obtained.

  On the other hand, when the frictional force is smaller than the excitation force, the inner coating layer 60A wears, and the damper contact surface 38 is exposed. If the frictional force between the damper contact surface 38 and the damper pin 50 is appropriate for the excitation force, frictional damping against the excitation force can be applied. That is, appropriate frictional damping can be given to an excitation force that is greater than expected. Thereby, it becomes possible to continue using the platform 32 without performing repair until the next maintenance time.

  In addition, the coating layer laminated | stacked on the damper contact surface 38 may be only one layer. In this case, the friction coefficient of the coating layer is set smaller than the friction coefficient of the damper contact surface 38. Three or more coating layers may be formed. In this case, the coating layer on the surface side is formed to have a smaller friction coefficient.

  In the second embodiment, the coating layer on the damper contact surface 38 may be formed only in a partial region in the axis O direction. When the wear of only a part of the damper contact surface 38 of the platform 32 in the axis O direction is likely to proceed, a coating layer is formed only on a part of the damper contact surface 38 in the direction of the axis O. Thus, wear can be effectively suppressed.

  In the second embodiment, the coating layer may be formed only on one of the damper contact surfaces 38 of the pair of damper contact surfaces 38 that face each other in the circumferential direction.

<Third embodiment>
Next, a third embodiment of the present invention will be described with reference to FIG. In 3rd embodiment, the same code | symbol is attached | subjected to the component similar to 1st, 2nd embodiment, and detailed description is abbreviate | omitted.
In the third embodiment, as in the second embodiment, two coating layers 70A and 70B having different friction coefficients are formed on the damper contact surface 38. Of these coating layers 70A and 70B, at least the outer coating layer 70B, that is, the outermost coating layer 70B is formed such that the friction coefficient gradually increases as the distance from the initial contact position P of the damper pin 50 increases. Yes. The initial contact position P is a position on the coating layers 70 </ b> A and 70 </ b> B where the damper pin 50 that receives a force radially outward by the centrifugal force contacts when no excitation force is applied.

  That is, the friction coefficients of the coating layers 70A and 70B on the damper contact surface 38 of the present embodiment are set to increase as the facing distance between the coating layers 70A and 70B facing each other in the circumferential direction increases. .

  As the excitation force increases, the amplitude of the damper pin 50 also increases, so that the damper pin 50 comes into contact with a wide range of the damper contact surface 38. That is, the contact position of the damper pin 50 with respect to the coating layers 70A and 70B changes from the initial contact position P. By setting the coefficient of friction of the coating layers 70A and 70B to increase according to the facing distance between the coating layers 70A and 70B, a large frictional force corresponding to the vibration amplitude is generated between the damper pin 50 and the damper contact surface 38. Can be made. That is, when the damper pin 50 is greatly shaken according to the excitation force, a larger frictional force can be generated on the damper pin 50. As described above, the coating layers 70 </ b> A and 70 </ b> B function as a stopper for the amplitude of the damper pin 50, thereby suppressing an increase in the vibration amplitude of the damper pin 50.

In the third embodiment, the coating layers 70 </ b> A and 70 </ b> B may be formed only on one damper contact surface 38 of the pair of damper contact surfaces 38 that face each other in the circumferential direction.
Further, the coating layers 70A and 70B do not have to have a two-layer structure, but only one layer. Three or more layers may be formed.
Further, in the first, second, and third embodiments, only one of the pair of damper contact surfaces 38 may be inclined and the other may be configured along the radial direction.

<Fourth embodiment>
Next, a fourth embodiment will be described with reference to FIG. In the fourth embodiment, the same components as those in the first to third embodiments are denoted by the same reference numerals, and detailed description thereof is omitted.
In the fourth 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 upper surface 101, the groove bottom surface 102, and the groove lower surface 103 which are the inner surfaces of the groove 100. A plurality of such leaf spring dampers 110 are provided corresponding to each leaf spring accommodating space R2.

Here, in this embodiment, the friction coefficient of the outer surface of the leaf spring damper body 111 on which the coating layer 112 is laminated is larger than the friction coefficient of the material forming the coating layer 112. That is, the material of the coating layer 112 that covers the leaf spring damper main body 111 has a smaller coefficient of friction than the surface of the leaf spring damper main body 111.
The leaf spring damper main body 111 is made of, for example, a material having a larger friction coefficient than the material forming the coating layer 112. Thereby, the friction coefficient of the outer surface of the leaf spring damper body 111 is larger than the friction coefficient of the coating layer 112. Further, the friction coefficient of the leaf spring damper main body 111 may be set to be larger than the friction coefficient of the coating layer 112 by roughing the outer surface of the leaf spring damper main body 111 by, for example, machining or chemical treatment.

<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 10, the outer surface of the leaf spring damper 110 slides with respect to the inner surface of the groove portion 100, and a friction force is generated between the leaf spring damper 110 and the inner surface of the groove portion 100. Thereby, the damping effect of the vibration by the friction force can be obtained.

  As in the first embodiment, when the excitation force is larger than expected, the coating layer 112 is worn and the outer surface of the leaf spring damper body 111 is exposed. And a frictional force generate | occur | produces between the outer surface with a large frictional force in the leaf | plate spring damper main body 111, and the inner surface of the groove part 100, and friction damping can be obtained. When the friction force is suitable for the applied excitation force, an appropriate damping effect can be obtained. As a result, the leaf spring damper 110 can be used without any repair until the next maintenance time.

Also in this embodiment, a plurality of coating layers 112 may be formed. In this case, the friction force is set to be smaller for the outer coating layer 112.
Further, the coating layer 112 may be formed only in a partial region of the leaf spring damper main body 111 in the direction of the axis O.

Further, the coating layer 112 may be formed on the inner surface of the groove 100. In this case, the friction coefficient of the coating layer 112 is set smaller than the friction coefficient of the inner surface of the groove part 100. This also has the same effect as described above. Further, the coating layer 112 on the inner surface of the groove 100 may be formed from a plurality of layers. In this case, the friction coefficient of the coating layer 112 on the surface side becomes smaller.
Note that the coating layer 112 may be formed only in a partial region of the inner surface of the groove 100 in the direction of the axis O.

<Fifth embodiment>
Next, a fifth embodiment will be described with reference to FIGS. In the fifth embodiment, the same components as those in the other embodiments are denoted by the same reference numerals, and detailed description thereof is omitted.
The turbine rotor blade 30 of the fifth 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 this embodiment, the friction coefficient of the side surface 121 of the shroud 120 on which the coating layer 140 is laminated is larger than the friction coefficient of the material forming the coating layer 140. That is, the material of the coating layer 140 that covers the side surface 121 of the shroud 120 has a smaller coefficient of friction than the side surface 121 of the shroud 120.
The side surface 121 of the shroud 120 is formed of, for example, a material having a larger friction coefficient than the material forming the coating layer 140. Thereby, the friction coefficient of the side surface 121 of the shroud 120 is larger than the friction coefficient of the coating layer 140. Further, the side surface 121 of the shroud 120 may be roughened by, for example, machining or chemical treatment, so that the friction coefficient of the side surface 121 of the shroud 120 may be set larger than the friction coefficient of the coating layer.

<Effect>
In the present embodiment, when an excitation force acts on the turbine rotor blade 30, a damping effect can be imparted by the friction force between the contact surfaces 130 of each friction damper 150.
Even when the excitation force is larger than expected, frictional damping can be obtained by the frictional force caused by the side surface 121 of the shroud 120 exposed after the coating layer 140 is worn. In addition, since the friction coefficient of the side surface 121 of the shroud 120 is larger than that of the coating layer 140, it is possible to give appropriate attenuation to an excitation force larger than expected.

  The coating layer 140 may be formed from a plurality of layers. In this case, the outer surface of the outermost coating layer 140 becomes the contact surface 130. Further, the friction coefficient is set to be smaller for the coating layer 140 on the front side.

<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 11a Disk 12 Turbine casing 13 Turbine static Blade stage 14 Turbine stationary blade 20 Turbine blade stage 30 Turbine 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 Blade body 50 Damper pin (Damper member)
51 Damper pin main body 52 Coating layer 60A Coating layer 60B Coating layer 70A Coating layer 70B Coating layer 101 Groove top surface 102 Groove bottom surface 103 Groove bottom 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 Housing Space R2 Leaf Spring Housing Space O Axis P Initial Contact Position

Claims (7)

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 abut against both platforms of the adjacent blades;
With
The damper member is
A damper member body;
And a coating layer that covers a surface of the damper member main body and is formed of a material having a smaller coefficient of friction than the damper member main body. 2. The rotating machine according to claim 1, wherein the damper member main body extends in the axial direction, and the coating layer is formed only in a partial region of the outer peripheral surface of the damper member main body in the axial direction. 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 coating layer formed on the surface of the platform and having a smaller coefficient of friction than the surface of the platform;
A plurality of damper members provided between the adjacent blades, the surfaces of which are in contact with both of the coating layers on the platforms of the adjacent blades;
Rotating machine with The damper member body has a pin shape extending in the axial direction,
The platform has a damper contact surface in which the opposing distance in the circumferential direction decreases as it goes radially outward between adjacent platforms,
The coating layer is formed on the surface of the damper contact surface,
4. The rotating machine according to claim 3, wherein a friction coefficient of the coating layer increases as a facing distance between the coating layers facing in the circumferential direction increases. The damper member main body extends in the axial direction,
The platform has a damper contact surface;
5. The rotating machine according to claim 3, wherein the coating layer is formed only in a partial region in the axial direction of the damper contact surface of the platform. 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
It has a contact surface that constitutes a friction damper by abutting each other between adjacent shrouds,
The contact surface is a rotating machine formed by a coating layer that is laminated on a surface of a shroud and has a smaller friction coefficient than the surface of the shroud. The coating layer is formed in a plurality of layers,
The rotating machine according to claim 1, wherein each of the coating layers has a smaller coefficient of friction as the coating layer on the surface side.

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