JP7235536B2 - rotating machinery - Google Patents

Description

The present invention relates to rotary machines.

2. Description of the Related Art In rotating machines such as gas turbines and jet engines, there is known a configuration in which dampers are provided between adjacent turbine rotor blades. The damper contacts the turbine rotor blades as the rotating machine rotates. When the excitation force acts on the turbine rotor blade and causes vibration, the vibration is attenuated by the frictional force at the contact point between the damper and the turbine rotor blade.
For example, U.S. Pat. No. 6,300,000 discloses a rotary machine with damper pins that contact the platforms of adjacent turbine rotor blades.

JP 2016-217349 A

By the way, the damper pin wears due to the frictional force between the damper pin and the platform. In particular, when the cross-sectional shape of the damper pin is circular, the damper pin and the platform are in line contact, so the surface pressure that the damper pin receives increases. Therefore, wear of the damper pin surface progresses more easily. If the wear of the damper pin progresses, the damping characteristics of the damper pin may change, and it may not be possible to impart an appropriate damping effect to the excitation force.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a rotating machine capable of suppressing progress of wear of a damper pin.

In order to solve the above problems, the present invention employs the following means. That is, a rotary machine according to a first aspect of the present invention includes a rotating shaft that rotates about an axis, and a plurality of rotor blades that are arranged in the circumferential direction on the outer peripheral side of the rotating shaft, and are attached to the rotating shaft. a blade having a root, a platform provided radially outward of the blade root, and a blade body extending radially outward from the platform; and a damper pin mounted on the platform, wherein the platforms are flat and extend in the axial direction, and the adjacent platforms face each other in the circumferential direction and approach the opposing platforms as they extend radially outward. The damper pin extends in the axial direction, and the centrifugal force caused by the rotation of the rotating shaft moves the center of gravity of the damper pin.

According to the rotating machine of the above aspect, the center of gravity is moved by the centrifugal force acting on the damper pin, so that the contact area between the damper pin and the damper contact surface can be increased step by step, and the frictional damping can reach the required area. , the wear of the damper pin can be suppressed. In addition, when the centrifugal force increases, the contact area between the damper pin and the damper contact surface increases, so the contact between the damper pin and the damper contact surface changes from line contact to surface contact, which reduces the surface pressure. It is possible to suppress the wear of the damper pin.

According to the second aspect of the present invention, the damper pin of the rotary machine according to the first aspect has an elastic member which is a plate material and has a spiral cross section, and the thickness of the elastic member increases toward the center. good too. With this configuration, centrifugal force acts on the center of the elastic member, which is the center of gravity. At this time, the center of the spiral, which is the position of the center of gravity, is displaced radially outward due to the action of the centrifugal force, which increases the amount of deformation of the elastic member. As a result, the surface pressure acting on the outer peripheral surface of the elastic member can be reduced. As a result, it is possible to prevent the wear of the damper pin from progressing at an early stage.

In addition, by forming the elastic member in a spiral shape, when centrifugal force acts on the elastic member, the elastic members come into contact with each other inside the elastic member, generating friction. As a result, a vibration damping effect can be obtained, so that it is possible to suppress the occurrence of wear on the outer peripheral surface of the elastic member.

According to the third aspect of the present invention, the damper pin according to the first aspect includes an elastic member that is a plate material and has a spiral cross section, and a core member attached to the center of the elastic member. good. With this configuration, when a centrifugal force acts on the core member located at the center of gravity, the core member is displaced radially outward and the elastic member is elastically deformed. This makes it possible to reduce the surface pressure acting on the outer peripheral surface of the elastic member. As a result, it is possible to prevent the wear of the damper pin from progressing at an early stage.

Further, by forming the elastic member in a spiral shape, the elastic members come into contact with each other or the core member and the elastic member inside the damper pin to generate friction. As a result, a vibration damping effect can be obtained, so that it is possible to suppress the occurrence of wear on the outer peripheral surface of the elastic member.

Further, a centrifugal force acts on the core member located at the center of gravity, and the core member moves radially outward, so that the inside of the damper pin comes into contact with the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin can be increased step by step, the wear of the elastic member and the core member can be suppressed until the vibration damping due to the friction inside the damper pin becomes necessary. . Moreover, since the characteristics of the damper pin can be changed by changing the weight of the core member, it is possible to configure the damper pin in accordance with the vibration characteristics of the rotor blade.

According to the fourth aspect of the present invention, the elastic member according to the second aspect or the third aspect is bent at the outer peripheral side end portion so that the outer peripheral side end portion becomes the inner peripheral side of the elastic member. may be in contact.

With this configuration, when the elastic member is deformed in the circumferential direction, friction occurs between the end portion on the outer peripheral side and the inner elastic member, a vibration damping effect can be obtained, and the outer peripheral surface of the elastic member is worn. can promote the suppression of Further, centrifugal force acts on the center of the damper pin, elastically deforming the damper pin, and the contact between the damper contact surface and the damper pin changes from line contact to surface contact. As a result, the contact area between the rotor blade and the damper pin is increased, so that the surface pressure is reduced and the wear of the damper pin can be suppressed.

Further, a centrifugal force acts on the core member located at the center of gravity, and the core member moves radially outward, so that the inside of the damper pin comes into contact with the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin can be increased step by step, the wear of the elastic member and the core member can be suppressed until the vibration damping due to the friction inside the damper pin becomes necessary. . Moreover, since the characteristics of the damper pin can be changed by changing the weight of the core member, it is possible to configure the damper pin in accordance with the vibration characteristics of the rotor blade.

According to a fifth aspect of the present invention, the damper pin according to the second aspect or the third aspect may further have a hollow cylindrical member provided on the outer periphery of the elastic member. With this configuration, by providing a cylindrical member on the outer periphery of the elastic member, vibration due to friction between the outer peripheral surface of the damper pin and the damper contact surface due to the deformation amount of the elastic member and the change in the contact angle with the damper contact surface Variation in the damping effect is suppressed, and stable vibration damping performance can be exhibited.

Further, by forming the elastic member in a spiral shape, the elastic members come into contact with each other or the core member and the elastic member inside the damper pin to generate friction. Thereby, a vibration damping effect can be obtained.

Further, a centrifugal force acts on the core member located at the center of gravity, and the core member moves radially outward, so that the inside of the damper pin comes into contact with the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin can be increased step by step, the wear of the elastic member and the core member can be suppressed until the vibration damping due to the friction inside the damper pin becomes necessary. . Moreover, since the characteristics of the damper pin can be changed by changing the weight of the core member, it is possible to configure the damper pin in accordance with the vibration characteristics of the rotor blade.

According to the sixth aspect of the present invention, a plurality of damper pins may be arranged inside the cylindrical member according to the fifth aspect. With this configuration, the performance of the plurality of sets of elastic members and core members inserted into the cylindrical member can be averaged, and vibration damping performance can be stabilized. Further, by changing the number of elastic members and core members inserted into the cylindrical member without changing the design of the elastic members and core members, the vibration damping characteristics of the damper pin can be changed.

In addition, by providing a cylindrical member on the outer periphery of the elastic member, the vibration damping effect is achieved by the friction between the outer peripheral surface of the damper pin and the damper contact surface due to the deformation amount of the elastic member and the change in the contact angle with the damper contact surface. variation is suppressed, and stable vibration damping performance can be exhibited.

Further, by forming the elastic member in a spiral shape, the elastic members come into contact with each other or the core member and the elastic member inside the damper pin to generate friction. Thereby, a vibration damping effect can be obtained.

Furthermore, centrifugal force acts on the core member, which is the position of the center of gravity of each group, and the core member moves radially outward, so that the inside of the damper pin comes into contact from the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin can be increased step by step, the wear of the elastic member and the core member can be suppressed until the vibration damping due to the friction inside the damper pin becomes necessary. . Moreover, by adjusting the weight of the core member to be inserted, the vibration damping characteristics of the damper pin can be adjusted.

According to a seventh aspect of the present invention, a rotary machine includes a rotating shaft that rotates about an axis, and a plurality of moving blades that are arranged in a circumferential direction on the outer peripheral side of the rotating shaft, and are attached to the rotating shaft. a blade having a root, a platform provided radially outward of the blade root, and a blade body extending radially outward from the platform; and radially inward of the platform between adjacent blades, respectively. and a plurality of damper pins provided, wherein the platforms have a flat shape extending in the axial direction, and adjacent platforms face each other in the circumferential direction and face each other as they go radially outward. and the angle at which at least one of the plurality of damper pins contacts the damper contact surface is different from that of the other damper pins.

This configuration makes the natural frequency of the rotor blade non-uniform in the circumferential direction. As a result, a so-called mistuned structure can be applied to a vibration phenomenon called flutter that occurs during start-up or high-load operation of a rotating machine equipped with rotor blades, and can withstand a wide range of excitation forces of turbine rotor blades. Vibration damping can be effectively exhibited. Therefore, the vibration damping effect of the turbine rotor blade can be improved not only by the friction between the damper pin and the damper contact surface, so the wear of the damper pin can be suppressed.

According to the eighth aspect of the present invention, at least one of the plurality of damper pins according to the seventh aspect may be formed with different dimensions in the circumferential direction. With this configuration, the natural frequencies of the rotor blades with which the damper pins of different sizes abut differ, so that the natural frequencies of the rotor blades become non-uniform in the circumferential direction. As a result, a so-called mistuned structure can be applied to a vibration phenomenon called flutter that occurs during start-up or high-load operation of a rotating machine equipped with rotor blades, and vibrates against a wide range of excitation forces of the rotor blades. Attenuation can be effectively exhibited. Therefore, it is possible to improve the vibration damping effect of the moving blade without relying only on the friction between the damper pin and the damper contact surface, so it is possible to suppress the wear of the damper pin.

According to the ninth aspect of the present invention, at least one of the plurality of damper contact surfaces of the rotary machine according to the seventh aspect or the eighth aspect may have a different inclination angle. With this configuration, when the damper pin contacts damper contact surfaces having different inclination angles, the natural frequency of the rotor blade becomes non-uniform in the circumferential direction. As a result, a so-called mistuned structure can be applied to a vibration phenomenon called flutter, and vibration damping can be effectively exhibited for a wide range of excitation forces of the moving blade. Therefore, it is possible to improve the vibration damping effect of the moving blade without relying only on the friction between the damper pin and the damper contact surface, so it is possible to suppress the wear of the damper pin.

ADVANTAGE OF THE INVENTION According to the rotary machine of this invention, the rotary machine which can suppress progress of wear of a damper pin can be provided.

1 is a schematic longitudinal sectional view of a gas turbine according to a first embodiment; FIG. FIG. 2 is a schematic view of the rotor blade group of the gas turbine according to the first embodiment, viewed from the axial direction; FIG. 3 is an enlarged view of a main part of FIG. 2 and is a view of mutually adjacent platforms of the gas turbine according to the first embodiment viewed from the axial direction; (a), (b), and (c) are diagrams showing states of the damper pin according to the first embodiment when different centrifugal forces act. It is the figure which looked at the mutually adjacent platform of the gas turbine which concerns on 2nd embodiment from the axial direction. (a), (b), and (c) are diagrams showing states of the damper pin according to the second embodiment when different centrifugal forces act. It is the figure which looked at the damper pin which concerns on the modification of 2nd embodiment from the axial direction. It is the figure which looked at the damper pin which concerns on 3rd embodiment from the axial direction. It is the figure which looked at the damper pin which concerns on 4th embodiment from the axial direction. FIG. 12A and 12B are diagrams of mutually adjacent platforms of a gas turbine according to a fifth embodiment as seen from the axial direction, and (a) and (b) illustrate states in which damper pins with different diameters are in contact with the platforms. FIG. 12A and 12B are diagrams of mutually adjacent platforms of a gas turbine according to a sixth embodiment viewed from the axial direction, in which (a) and (b) are diagrams showing states in which damper pins are in contact with damper contact surfaces having different inclination angles; is.

<First embodiment>
A gas turbine 1 according to a first embodiment of the present invention will be described below with reference to FIGS. 1 to 4. FIG. FIG. 1 is a schematic longitudinal sectional view of the gas turbine according to the first embodiment. FIG. 2 is a schematic diagram of the moving blade group of the gas turbine according to the first embodiment as seen from the axial direction. FIG. 3 is an enlarged view of a main part of FIG. 2, and is a view of adjacent platforms of the gas turbine according to the first embodiment viewed from the axial direction. FIGS. 4A, 4B, and 4C are diagrams showing states of the damper pin according to the first embodiment when different centrifugal forces act.

As shown in FIG. 1, the gas turbine 1 according to the present embodiment includes a compressor 2 that generates compressed air, a combustor 9 that mixes and burns fuel in the compressed air to generate combustion gas, a turbine 10 driven by gas.

The compressor 2 has a compressor rotor 3 that rotates around an 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. As shown in FIG. A plurality of compressor rotor blade stages 5 arranged at intervals in the direction of the axis O are provided on the outer peripheral surface of the compressor rotor 3 . Each compressor rotor blade stage 5 has a plurality of compressor rotor blades 6 circumferentially spaced about the axis O on the outer peripheral surface of the compressor rotor 3 .

The compressor casing 4 has a tubular shape centered on the axis O. As shown in FIG. A plurality of compressor stator 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 stator blade stages 7 are alternately arranged with respect to the compressor rotor blade stages 5 when viewed from the axis O direction. Each compressor stator vane stage 7 has a plurality of compressor stator vanes 8 arranged on the inner peripheral surface of the compressor casing 4 at intervals in the circumferential direction of the axis O. As shown in FIG.

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

The turbine 10 has a turbine rotor 11 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. As shown in FIG. A plurality of turbine rotor blade stages 20 arranged at intervals in the direction of the axis O are provided on the outer peripheral surface of the turbine rotor 11 . Each turbine rotor blade stage 20 has a plurality of turbine rotor blades 30 arranged at intervals in the circumferential direction of the axis O on the outer peripheral surface of the turbine rotor 11 . The turbine rotor 11 is integrally connected to the compressor rotor 3 in the direction of the axis O to form a gas turbine rotor.

The turbine casing 12 has a tubular shape centered on the axis O. As shown in FIG. A plurality of turbine stator 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 stator blade stages 13 are alternately arranged with respect to the turbine rotor blade stages 20 when viewed from the axis O direction. Each turbine stator vane stage 13 has a plurality of turbine stator vanes 14 arranged on the inner peripheral surface of the turbine casing 12 at intervals in the circumferential direction of the axis O. As shown in FIG. 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 described above is integrally rotatable about the axis O within the gas turbine casing.

<Turbine rotor blade>
Next, the turbine rotor blade 30 will be described in more detail with reference to FIG.
The turbine rotor blade 30 has a blade root 31 , a platform 32 and a blade body 41 .
The blade root 31 is a portion of the turbine rotor blade 30 that is attached to the turbine rotor 11 . The turbine rotor 11 is configured by stacking a plurality of disk-shaped disks 11a centered on the axis O in the direction of the axis O. As shown in FIG. The blade root 31 is integrally attached to the disk 11a by being fitted in the groove (not shown) of the disk 11a formed on the outer peripheral surface of the disk 11a from the direction of the axis O. As shown in FIG. As a result, the turbine rotor blades 30 are radially arranged so as to be circumferentially spaced from the disk 11a.

The platform 32 is integrally provided radially outward 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. A radially outwardly facing outer peripheral surface 33 of the platform 32 is exposed to the combustion gases passing through the turbine 10 .

A circumferentially facing platform side 34 of the platform 32 extends radially and in the direction of the axis O. As shown in FIG. The platform side surfaces 34 of the platforms 32 of the turbine rotor blades 30 adjacent to each other face each other in the circumferential direction.

One of the platform side surfaces 34 facing each other in the circumferential direction is formed with a recessed portion 37 recessed from the platform side surface 34 and extending in the direction of the axis O. As shown in FIG. A damper accommodation space R1 extending through the platform 32 in the direction of the axis O is defined according to the shape of the recess 37 . A damper accommodation space R1 is formed in one of all adjacent platform side surfaces 34 . Therefore, the same number of damper accommodation spaces R1 as the number of turbine rotor blades 30 are formed.

Each platform side 34 is radially divided by a recess 37 . Of the platform side surface 34 , the radially outer portion of the recess 37 is defined as an outer peripheral side surface 35 , and the radially inner portion of the recessed portion 37 is defined as an inner peripheral side surface 36 .

As shown in FIGS. 2 and 3 , the surface of the concave portion 37 of the platform 32 facing radially inward serves as a damper contact surface 38 . The damper contact surface 38 has a planar shape parallel to the axis O. As shown in FIG. The damper contact surface 38 is connected to the outer peripheral side surface 35 of the platform 32 while extending obliquely outward in the radial direction toward the opposing platform side surface 34 .

As shown in FIGS. 2 and 3, the end of the damper contact surface 38 opposite to the outer peripheral side surface 35 is connected to the radially outer end of the recess bottom surface 39 extending radially in parallel with the axis O. It is A recess bottom surface 40 extending in parallel to the axis O and 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 circumferential side surface 36 . The damper housing space R<b>1 is defined by a damper contact surface 38 , a recess bottom surface 39 and a recess bottom surface 40 .

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 blade body 41 has an airfoil shape in cross section perpendicular to the extending direction of the blade body 41 .

<Dumper pin>
As shown in FIGS. 2 and 3, a damper pin 50 is accommodated in each damper accommodation space R1. That is, the same number of damper pins 50 as the damper housing space R1 are provided corresponding to the damper housing space R1. The damper pin 50 has a columnar elastic member 51 extending in the axis O direction. The damper pin 50 has a uniform cross-sectional shape perpendicular to the axis O over the axis O direction.

The elastic member 51 is a plate material and has a spiral shape with an axis extending in the circumferential direction, so that the cross section thereof has a spiral shape. As a result, the radially inner end of the elastic member becomes the center of the spiral. That is, the elastic member 51 is formed to have a circular and spiral cross-sectional shape by being wound a plurality of times. Also, the elastic member 51 is configured such that its thickness increases toward the center of the spiral.

<Action and effect>
When the turbine 10 rotates, centrifugal force is generated in the damper pin 50 and the outer peripheral surface of the damper pin 50 contacts the damper contact surface 38 . Here, when the damper pin 50 is a metallic cylindrical pin as in the prior art, the damper pin 50 is in line contact with the damper contact surface 38 . As a result, a large surface pressure acts on the damper pin 50, and as a result, the damper pin 50 wears out quickly.

In the present embodiment, the damper pin 50 is configured by an elastic member 51 that can be elastically deformed, and the thickness increases toward the center of the elastic member 51, so that the center of the spiral of the elastic member 51, which is the center of gravity, is the center of the centrifugal force. force acts.

In this case, as shown in FIG. 4(a), when the centrifugal force acting on the damper pin 50 is small, the elastic member 51 is partially deformed inside and contacts, but the outer shape maintains its original shape. The damper contact surface 38 and the damper pin 50 are in line contact.

Next, as shown in FIG. 4(b), when the centrifugal force acting on the damper pin 50 becomes greater than in FIG. 4(a), the center of the spiral of the damper pin 50 moves radially outward. At this time, the outer shape of the elastic member 51 is deformed, and the contact between the damper contact surface 38 and the damper pin 50 changes from line contact to surface contact.

Then, as shown in FIG. 4(c), when the centrifugal force acting on the damper pin 50 becomes greater than in FIG. 4(b), the displacement of the spiral center of the damper pin 50 further increases. Along with this, the contact area between the damper contact surface 38 and the damper pin 50 further increases, and the surface pressure further decreases.

As a result, centrifugal force acts on the damper pin 50, and as the center of the thick spiral moves radially outward, the contact between the damper pin 50 and the damper contact surface 38 changes from line contact to surface contact. The surface pressure acting on the damper pin 50 can be reduced. Therefore, it is possible to prevent the wear of the damper pin 50 from advancing at an early stage.

Further, by forming the elastic member 51 in a spiral shape, when centrifugal force acts on the elastic member 51, the elastic members 51 come into contact with each other inside the elastic member 51, generating friction. As a result, a vibration damping effect can be obtained, so that the outer peripheral surface of the elastic member 51 can be prevented from being worn.

Furthermore, the centrifugal force causes the center of the spiral, which is the position of the center of gravity, to be displaced radially outward step by step, thereby increasing the frictional attenuation occurring inside the elastic member 51 step by step. As a result, it is possible to suppress wear inside the elastic member 51 up to a region where frictional attenuation is required inside the elastic member 51 . In addition, a portion of the elastic member 51 having a large thickness requires a large force for deformation. As a result, inside the elastic member 51, contact can be made from the outer peripheral side where the contact area is large, so that the vibration damping effect can be efficiently obtained. In addition, since the damper pin 50 is composed of the elastic member 51 alone, it has an advantage of excellent workability.

The first embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, the damper pin 50 is not limited to the above configuration as long as it is elastically deformable and is configured to generate friction inside.

<Second embodiment>
Next, a second embodiment of the present invention will be described with reference to FIGS. 5 to 7. FIG. In the second embodiment, components similar to those in the first embodiment are denoted by the same reference numerals, and detailed descriptions thereof are omitted. FIG. 5 is an axial view of adjacent platforms of the gas turbine according to the second embodiment. 6(a), (b), and (c) are diagrams showing states of the damper pin according to the second embodiment when different centrifugal forces act. FIG. 7 is an axial view of a damper pin according to a modification of the second embodiment. The damper pin 60 of the second embodiment has an elastic member 52 having a spiral cross section and a metal core 54 that is a core member attached to the center of the elastic member 52 .

As shown in FIG. 4, the elastic member 52 has a uniform thickness, and a pin-shaped metal core 54 extending in the direction of the axis O is attached to the center of the spiral of the elastic member 52 . The metal core 54 is a core member provided so as to be positioned at the center of the damper pin 60, and has a circular cross section.

<Action and effect>
According to the above configuration, centrifugal force acts on the metal core 54, which is the center of gravity. In this case, as shown in FIG. 6A, when the centrifugal force acting on the metal core is small, the damper pin maintains its original shape, and the damper pin 60 and the damper contact surface 38 are in line contact.

Next, as shown in FIG. 6(b), when the centrifugal force acting on the damper pin 60 becomes greater than that in FIG. 6(a), the metal core 54 moves radially outward. At this time, the elastic member 52 connected to the metal core 54 is deformed, and the damper pin 60 comes into surface contact with the damper contact surface 38 . At this time, the surface pressure acting on the damper pin 60 is reduced as compared with the case of FIG. 6(a).

Then, as shown in FIG. 6C, when the centrifugal force acting on the damper pin 60 further increases, the metal core 54 largely moves radially outward. Accordingly, the amount of deformation of the elastic member 52 further increases, and the contact area between the damper contact surface 38 and the damper pin 60 further increases. At this time, the surface pressure acting on the damper pin 60 is further reduced than in FIG. 6(b).

As a result, a centrifugal force acts on the metal core 54, and as the metal core 54 is displaced radially outward, the amount of deformation of the elastic member 52 increases. At this time, the contact between the damper contact surface 38 and the damper pin 60 changes from line contact to surface contact, and the surface pressure acting on the outer peripheral surface of the elastic member 52 can be reduced. It can be suppressed.

Further, by forming the elastic member 52 in a spiral shape, the elastic members 52 come into contact with each other or the metal core 54 and the elastic member 52 inside the damper pin 60 to generate friction. As a result, a vibration damping effect can be obtained, so that the outer peripheral surface of the elastic member 52 can be prevented from being worn.

Furthermore, a centrifugal force acts on the metal core 54 at the center of gravity, and the metal core 54 moves radially outward, so that the inside of the damper pin 60 comes into contact with the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin 60 can be increased step by step, the wear of the elastic member 52 and the metal core 54 is suppressed until the vibration damping due to the friction inside the damper pin 60 becomes necessary. can do.

Moreover, since the characteristics of the damper pin 60 can be changed by changing the weight of the metal core 54 , the damper pin 60 can be designed according to the vibration characteristics of the turbine rotor blade 30 .

<Modification>
The second embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention.
For example, as a modification of the second embodiment, as shown in FIG. 7, the end portion of the elastic member 53 on the outer peripheral side is bent so as to contact the elastic member 53 inside the end portion. Also good. In this case, in addition to the above effects, when the elastic member 53 is deformed in the circumferential direction, friction is generated between the end portion on the outer peripheral side and the inner elastic member 53, and a vibration damping effect can be obtained. It is possible to promote suppression of wear of the outer peripheral surface of the elastic member 53 . As in the modified example, the elastic member 51 of the first embodiment can also be configured such that the end portion on the outer peripheral side is bent so as to contact the elastic member 51 on the inner peripheral side. In this case, the damper pin has the same effect as the modified example.

Note that the metal core 54 does not have to have a circular cross section, and can have various configurations such as a polygonal shape depending on the design. Furthermore, the core used for the damper pin 60 does not necessarily have to be made of metal, and is not particularly limited as long as it has a configuration that exhibits the above effects.

<Third embodiment>
A third embodiment of the present invention will be described below with reference to FIG. In the third embodiment, components similar to the components described above are denoted by the same reference numerals, and detailed descriptions thereof are omitted. FIG. 8 is an axial view of the damper pin according to the third embodiment. As shown in FIG. 8, the damper pin 80 of the third embodiment has a hollow cylindrical member 58 on the outer circumference of the elastic member 52 in addition to the configuration of the second embodiment. The cylindrical member 58 extends in the direction of the axis O and has a cylindrical shape and is hollow. The cylindrical member 58 is made of a material that deforms less than the elastic member 52 due to centrifugal force.

<Action and effect>
According to the above configuration, by providing the cylindrical member 58 on the outer periphery of the elastic member 52, variations in the vibration damping effect due to the amount of deformation of the elastic member 52 and changes in the contact angle with the damper contact surface 38 are suppressed, and the vibration damping effect is stabilized. It is possible to demonstrate the vibration damping performance.

Furthermore, by forming the elastic member 52 in a spiral shape, the elastic members 52 come into contact with each other or the metal core 54 and the elastic member 52 inside the damper pin 80 to generate friction. Thereby, a vibration damping effect can be obtained.

Furthermore, centrifugal force acts on the metal core 54 at the center of gravity, and the metal core 54 moves radially outward, so that the inside of the damper pin 80 comes into contact with the outer peripheral side where the contact area is large. Therefore, since the vibration damping effect due to the friction generated inside the damper pin 80 can be increased step by step, the wear of the elastic member 52 and the metal core 54 is suppressed until the vibration damping due to the friction inside the damper pin 80 becomes necessary. can do.

Moreover, since the characteristics of the damper pin 50 can be changed by changing the weight of the metal core 54 , the damper pin 50 can be designed according to the vibration characteristics of the turbine rotor blade 30 .

The third embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, a cylindrical member can be combined with the elastic member of the first embodiment. In this case, similar to the present embodiment, the damper pin can suppress variations in vibration damping performance by applying a cylindrical member. Moreover, what is provided on the outer periphery of the elastic member 52 is not necessarily limited to a cylindrical member, and a polygonal member may be provided on the outer periphery of the elastic member 52 according to the design.

<Fourth embodiment>
A fourth embodiment of the present invention will now be described with reference to FIG. In the fourth embodiment, the same reference numerals are given to the same constituent elements as in the above-described embodiment, and detailed description thereof will be omitted. FIG. 9 is an axial view of a damper pin according to the fourth embodiment. As shown in FIG. 9, the damper pin 90 of the fourth embodiment differs from that of the third embodiment in that a plurality of sets of elastic members 52 and metal cores 54 are housed inside a hollow cylindrical member 58 . The cylindrical member 58 has a hollow region in which the elastic member 52 and the metal core 54 are inserted, and the other regions are solid. For example, three sets of cylindrical members 58 and metal cores 54 are inserted inside the cylindrical member 58, and these are arranged at regular intervals in the circumferential direction.

<Action and effect>
When only a set of elastic member 52 and metal core 54 is inserted inside the cylindrical member 58, the centrifugal force acts on the metal core 54 at the center of gravity. have a great impact on On the other hand, when a plurality of sets of the elastic member 52 and the metal core 54 are inserted, the movement of the metal core 54, which is the position of the center of gravity of each set, affects the cylindrical member 58 compared to when only one set is inserted. becomes smaller and averages out. As a result, the vibration damping performance of the damper pin 90 can be stabilized.

Furthermore, by changing the numbers of the elastic members 52 and the metal cores 54 inserted into the cylindrical member 58 without changing the design of the elastic members 52 and the metal cores 54, the vibration damping characteristics of the damper pin 90 can be changed. can.

In addition, by providing the cylindrical member 58 on the outer periphery of the elastic member 52 , the amount of deformation of the elastic member 52 and the change in the contact angle with the damper contact surface 38 cause a difference between the outer peripheral surface of the damper pin 90 and the damper contact surface 38 . Variation in the vibration damping effect due to friction is suppressed, and stable vibration damping performance can be exhibited.

Furthermore, by forming the elastic member 52 in a spiral shape, the elastic members 52 come into contact with each other or the metal core 54 and the elastic member 52 inside the damper pin 90 to generate friction. Thereby, a vibration damping effect can be obtained.

Furthermore, centrifugal force acts on the metal core 54, which is the position of the center of gravity of each group, and the metal core 54 moves radially outward. become. Therefore, since the vibration damping effect due to the friction generated inside the damper pin 90 can be increased step by step, the wear of the elastic member 52 and the metal core 54 is suppressed until the vibration damping due to the friction inside the damper pin 90 becomes necessary. can do.

The fourth embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, the set of elastic members 52 and metal cores 54 are not necessarily arranged at equal intervals in the circumferential direction inside the cylindrical member 58, and the arrangement position can be arbitrarily changed according to the design. be. Also, by adjusting the weight of the metal core 54 to be inserted, the vibration damping characteristics of the damper pin 90 can be adjusted.

<Fifth embodiment>
Next, a fifth embodiment of the present invention will be described with reference to FIGS. 10(a) and 10(b). In the fifth embodiment, the same reference numerals are given to the same components as in the above embodiments, and detailed descriptions thereof are omitted. FIG. 10 is an axial view of adjacent platforms of a gas turbine according to a fifth embodiment, in which (a) and (b) show states in which damper pins with different diameters are in contact with the platforms. is.

As shown in FIGS. 10(a) and 10(b), in the fifth embodiment, at least one damper pin 50A among the damper pins housed in each damper housing space R1 and other damper pins 50B other than the damper pin 50A. have different structures. The damper pin 50A and the damper pin 50B are pin-shaped members extending in the direction of the axis O and have the same outer shape. On the other hand, the damper pin 50A and the damper pin 50B are formed with different dimensions. Specifically, the damper pins 50A and the damper pins 50B are formed to have different circumferential dimensions. At this time, the damper pin 50A and the damper pin 50B come into contact with the damper contact surface 38 at different contact angles.

<Action and effect>
According to the above configuration, the natural frequency of the turbine rotor blade 30 with which the damper pin 50A abuts differs from that of the turbine rotor blade 30 with which the damper pin 50B abuts. become uniform. As a result, a so-called mistuned structure can be applied to a vibration phenomenon called flutter that occurs during start-up of the gas turbine 1 including the turbine rotor blades 30 or during high-load operation. Vibration damping can be effectively exhibited against force. Therefore, the vibration damping effect of the turbine rotor blade 30 can be improved not only by the friction between the damper pin and the damper contact surface 38, so the wear of the damper pin can be suppressed.

The fifth embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, the contact angle between the damper pin and the damper contact surface may be changed by changing the outer shape of the damper pin. Also, all of the plurality of damper pins may be formed with different dimensions, or only some of them may be formed with different dimensions.

<Sixth embodiment>
A sixth embodiment of the present invention will now be described with reference to FIG. In the sixth embodiment, the same reference numerals are assigned to the same components as in the above embodiments, and detailed description thereof is omitted. 11A and 11B are diagrams of mutually adjacent platforms of a gas turbine according to the sixth embodiment as seen from the axial direction, and in FIGS. 11A and 11B, damper pins are in contact with damper contact surfaces having different inclination angles. It is a figure which shows a state.

As shown in FIGS. 11A and 11B, in the sixth embodiment, the inclination angle θ1 of at least one damper contact surface 38A of the damper contact surfaces 38 forming each recess 37 and the damper The inclination angle θ2 of the damper contact surface 38B other than the contact surface 38A is different. Specifically, the angle formed by the damper contact surface 38A and the axis perpendicular to the radial direction is different from the angle formed by the damper contact surface 38B and the axis perpendicular to the radial direction. At this time, the damper contact surface 38A and the damper contact surface 38B contact the damper pin 100 at different contact angles.

<Action and effect>
According to the above configuration, when the damper pin 100 contacts, the turbine rotor blade 30 having the damper contact surface 38A and the turbine rotor blade 30 having the damper contact surface 38B have different natural frequencies. The natural frequency of the rotor blade 30 becomes non-uniform in the circumferential direction. As a result, a so-called mistuned structure can be applied to a vibration phenomenon called flutter, and vibration damping can be effectively exhibited for a wide range of excitation forces of the turbine rotor blade 30 . Therefore, the vibration damping effect of the turbine rotor blade 30 can be improved not only by the friction between the damper pin and the damper contact surface, so the wear of the damper pin can be suppressed.

The fifth embodiment of the present invention has been described above with reference to the drawings. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, all the damper contact surfaces may have different inclination angles, or some of the damper contact surfaces may have different inclination angles.

<Other embodiments>
Although the embodiments of the present invention have been described above with reference to the drawings, the specific configuration is not limited to these embodiments, and includes design changes and the like within the scope of the present invention. be For example, in the embodiment, an example in which the present invention is applied to the turbine rotor blades 30 of the gas turbine 1 has been described, but the present invention can also be applied to rotor blades of other rotating machines such as jet engine rotor blades and steam turbine rotor blades. may apply.

1 gas turbine 2 compressor 3 compressor rotor 4 compressor casing 5 compressor rotor blade stage 6 compressor rotor blade 7 compressor stator blade stage 8 compressor stator blade 9 combustor 10 turbine 11 turbine rotor 11a disk 12 turbine casing 13 turbine stator Blade stage 14 Turbine stationary blade 20 Turbine rotor blade stage 30 Turbine rotor blade 31 Blade root 32 Platform 33 Outer peripheral surface 34 Platform side surface 35 Outer peripheral side surface 36 Inner peripheral side surface 37 Concave portion 38 Damper contact surface 39 Concave bottom surface 40 Concave lower surface 41 Blade Body 50, 60, 70, 80, 90, 100, 50A, 50B Damper pin 51, 52, 53 Elastic member 54 Metal core 58 Cylindrical member R1 Damper accommodation space θ1, θ2 Tilt angle O Axis

Claims (6)

a rotating shaft that rotates about an axis;
A plurality of moving blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, comprising a blade root attached to the rotating shaft, a platform provided radially outward of the blade root, and radially outward from the platform. a rotor blade having a blade body extending into
a damper pin provided radially inward of the platform between the rotor blades adjacent to each other;
with
The platform is
a damper abutment surface extending in the axial direction and having a damper abutment surface that is circumferentially opposed to the adjacent platforms and extends toward the opposing platforms toward the radially outer side;
The damper pin extends in the axial direction,
The damper pin is
an elastic member that is a plate material and has a spiral cross section;
a core member attached to the center of the elastic member;
a hollow columnar member provided on the outer periphery of the elastic member;
has
Centrifugal force accompanying the rotation of the rotating shaft acts on the core member, whereby the core member moves radially outward relative to the columnar member that contacts the damper contact surface.
rotating machinery. a rotating shaft that rotates about an axis;
A plurality of rotor blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, comprising a blade root attached to the rotating shaft, a platform provided radially outward of the blade root, and radially outward from the platform. a rotor blade having a blade body extending into
a damper pin provided radially inward of the platform between the rotor blades adjacent to each other;
with
The platform is
a damper abutment surface extending in the axial direction and having a damper abutment surface that is circumferentially opposed to the adjacent platforms and extends toward the opposing platforms toward the radially outer side ;
The damper pin extends in the axial direction,
The damper pin has an elastic member that is a plate material and has a spiral cross section,
The thickness of the elastic member increases toward the center,
rotating machinery. The damper pin is
3. The rotary machine according to claim 2 , further comprising a hollow cylindrical member provided on the outer circumference of said elastic member. The rotary machine according to claim 3 , wherein a plurality of said damper pins are arranged inside said cylindrical member. a rotating shaft that rotates about an axis;
A plurality of rotor blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, comprising a blade root attached to the rotating shaft, a platform provided radially outward of the blade root, and radially outward from the platform. a rotor blade having a blade body extending into
a damper pin provided radially inward of the platform between the rotor blades adjacent to each other;
with
The platform is
a damper abutment surface extending in the axial direction and having a damper abutment surface that is circumferentially opposed to the adjacent platforms and extends toward the opposing platforms toward the radially outer side ;
The damper pin extends in the axial direction,
The damper pin has an elastic member that is a plate material and has a spiral cross section,
The thickness of the elastic member increases toward the center,
By bending the end portion on the outer peripheral side of the elastic member,
the end on the outer peripheral side is in contact with the inner peripheral side of the elastic member;
rotating machinery. a rotating shaft that rotates about an axis;
A plurality of moving blades arranged in a circumferential direction on the outer peripheral side of the rotating shaft, comprising a blade root attached to the rotating shaft, a platform provided radially outward of the blade root, and radially outward from the platform. a rotor blade having a blade body extending into
a damper pin provided radially inward of the platform between the rotor blades adjacent to each other;
with
The platform is
a damper abutment surface extending in the axial direction and having a damper abutment surface that is circumferentially opposed to the adjacent platforms and extends toward the opposing platforms toward the radially outer side ;
The damper pin extends in the axial direction,
The damper pin is
an elastic member that is a plate material and has a spiral cross section;
a core member attached to the center of the elastic member;
has
By bending the end portion on the outer peripheral side of the elastic member,
A rotary machine in which the end on the outer peripheral side is in contact with the inner peripheral side of the elastic member .

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