JP7022623B2 - Blades and rotary machines - Google Patents

Description

The present invention relates to a rotor blade and a rotating machine.

One of the rotary machines is a gas turbine. The gas turbine includes a compressor, a combustor, and a turbine.
The compressor produces high-temperature, high-pressure compressed air by compressing the air taken in from the air intake. The combustor generates high-temperature, high-pressure combustion gas (working fluid) by supplying fuel to compressed air and burning it. The turbine is driven by the combustion gas and also drives the generator connected to the turbine.

The compressor and turbine have a blade body. The rotor blade has a rotor disk that rotates integrally with the spindle, and a plurality of rotor blades that are assembled so as to extend radially from the outer peripheral portion of the rotor disk. The plurality of blades are each engaged with a groove formed in the outer peripheral portion of the rotor disk at each blade root portion.
In the rotor blade body having such a configuration, it is necessary to attenuate the vibration (natural vibration) of the rotor blade. For example, Patent Document 1 is a technique for attenuating the vibration of a moving blade.

In Patent Document 1, centrifugal force causes frictional damping by contacting a pair of platforms in a state where the gap formed between the pair of platforms adjacent to each other in the circumferential direction is closed and sliding to generate frictional damping. A blade body with a non-metallic seal pin that damps the vibration of the blade is disclosed.

Japanese Unexamined Patent Publication No. 2014-105705

By the way, in recent years, it has been desired to stably attenuate the vibration of the moving blade.

Therefore, an object of the present invention is to provide a rotor blade body and a rotary machine capable of stably damping the vibration of the rotor blade.

In order to solve the above problems, the rotor blade body according to one aspect of the present invention has a rotor disk having a plurality of fitting grooves formed on the outer peripheral portion and can rotate integrally with the main shaft, and the blade portion and the fitting groove. The rotor blades to be fitted, and a plurality of blades arranged between the blades and the blades and having a platform facing the outer peripheral surface of the rotor disk, and the rotor disk in the axial direction of the spindle. A sealing member that closes a gap formed between the outer peripheral surface of the surface and the platform, and the sealing member is provided from the rotor disk and the platform so as to be able to apply an elastic force to the platform. It is arranged between the platform and the rotor disk in a state of being curved so as to be convex in the direction of separation and elastically deformed , and one end of the sealing member is accommodated in the outer peripheral portion of the rotor disk. A first accommodating portion is formed, and a second accommodating portion in which the other end of the sealing member is accommodated is formed in a portion of the platform facing the first accommodating portion. The seal member is fixed from the inside in the radial direction by the first accommodating portion and is fixed from the outside in the radial direction by the second accommodating portion .

According to the present invention, it is arranged between the platform and the rotor disk in a state of being elastically deformed so that elastic force can be applied to the platform, and the outer peripheral surface of the rotor disk and the platform are arranged in the axial direction of the spindle. By having the sealing member that closes the gap formed between them, it is possible to always exert the elastic force of the sealing member on the moving blade.
As a result, when vibration is generated in the moving blade, the vibration of the moving blade can be stably damped by using the elastic force of the sealing member.
Further, by having the first and second accommodating portions having such a configuration, the sealing member can be arranged between the platform and the rotor disk.

Further, in the rotor blade body according to one aspect of the present invention, the width of the first accommodating portion in the axial direction is configured to be larger than the thickness of the one end portion of the sealing member. The width of the second accommodating portion in the axial direction is configured to be larger than the thickness of the other end portion of the sealing member, and the sealing member is deformed in the axial direction. It may be arranged in the first and second accommodating portions.

With such a configuration, one end of the seal member can be displaced in the axial direction within the width of the first accommodating portion, and within the width of the second accommodating portion. Allows the other end of the seal member to be displaced in the axial direction.
As a result, when the rotor blade vibrates, the seal member accommodated in the first and second accommodating portions can be displaced in the axial direction in a deformed state, so that the vibration of the rotor blade is stably damped. Can be made to.

Further, in the rotor blade body according to one aspect of the present invention, the seal member is inclined in a direction approaching the wing root portion in a state where one end portion is fitted to the first accommodating portion. The other end portion of the seal member may be fitted to the second accommodating portion so that the angle of inclination of the seal member with respect to the outer peripheral surface of the rotor disk is large.

In this way, in a state where one end of the seal member is fitted to the first accommodating portion, the other end portion of the seal member is inclined toward the wing root portion in the second accommodating portion. In the fitted state, the other end of the seal member is fitted to the second accommodating portion so that the angle of inclination of the seal member with respect to the outer peripheral surface of the rotor disk becomes large, so that the first and first portions are fitted. With the seal member fitted in the accommodating portion of 2, the restoring force of the seal member (the force that the seal member tends to tilt toward the wing root (the force that tries to return to the original tilted state)) is always the moving wing. Will be granted to.
As a result, when the moving blade vibrates, the vibration of the moving blade can be stably damped by the restoring force of the sealing member.

Further, in the rotor blade body according to one aspect of the present invention, a rotor disk having a plurality of fitting grooves formed on the outer peripheral portion and rotatable integrally with the spindle, a blade portion, and a blade fitted in the fitting groove. A plurality of blades arranged between the root portion and the wing portion and the wing root portion and having a platform facing the outer peripheral surface of the rotor disk, and the outer peripheral surface of the rotor disk and the outer peripheral surface of the rotor disk in the axial direction of the main axis. The platform comprises a sealing member that closes a gap formed between the platform and the platform, the platform has a first side surface arranged in the axial direction, and the rotor disk has the first side surface in the axial direction. It has a second side surface arranged on the same side as the side surface of the rotor disk, and the sealing member extends outward in the radial direction of the rotor disk and has a plate shape that can be elastically deformed in the axial direction. Of the thin-walled plate portion that is in contact with the rotor blade and whose position is restricted by the rotor disk to be a fixed end, and the end surface of the thin-walled plate portion that comes into contact with the first side surface. It is provided on a surface located on the side opposite to the surface in contact with the side surface of No. 1, is thicker than the thin-walled plate portion in the axial direction, and can be attached to and detached from the first side surface. It has a thick portion having a free end, and the thin plate portion is arranged with a gap in the axial direction with respect to the rotor disk.

In this way, the thin-walled plate portion that is elastically deformable in the axial direction, is in contact with the first side surface, and the position is restricted by the rotor disk, and the thin-walled plate portion that is in contact with the first side surface. By having a thick portion that is provided on a surface of the end surface that is located on the side opposite to the surface that comes into contact with the first side surface and that is thicker than the thin plate portion in the axial direction. The position of the center of gravity of the seal member can be arranged in the thick portion.

As a result, the position of the center of gravity of the seal member can be arranged in the axial direction away from the moving blades from the position of the fixed end of the seal member.
Then, when the rotor disk rotates, centrifugal force is applied to the seal member at the center of gravity (point of action) of the seal member. As described above, the center of gravity of the seal member is located in the axial direction away from the moving blade with respect to the fixed end of the seal member.

Therefore, when a centrifugal force is applied to the center of gravity of the seal member, the first moment acting in the direction from the fixed end of the seal member toward the center of gravity of the seal member and the direction orthogonal to the direction in which the first moment acts. Then, a second moment M2 acting in the direction toward the moving blade is generated.
Therefore, when the rotor blade vibrates during the rotation of the rotor disk, the vibration of the rotor blade can be stably damped by the second moment.

Further, in the rotor blade body according to one aspect of the present invention, the thin-walled plate portion may be fixed to the second side surface of the rotor disk.

By fixing the thin-walled plate portion to the second side surface of the rotor disk in this way, when centrifugal force is generated, the portion of the thin-walled plate portion that is not fixed to the rotor disk (thick-walled portion is arranged). The part) can be elastically deformed.

Further, in the rotor blade body according to one aspect of the present invention, the seal member may be integrally formed with the rotor disk.

By forming the seal member integrally with the rotor disk in this way, when centrifugal force is generated, the portion of the seal member protruding from the rotor disk (the portion where the thick portion is arranged) is elastically deformed. Can be done.

Further, in the rotor blade body according to one aspect of the present invention, the thin-walled plate portion is integrally formed with the first plate portion extending in the axial direction and the first plate portion, and is radially outside the rotor disk. It has a second plate portion extending to and abutting on the first side surface, and an end portion of the first plate portion is fitted to the second side surface side of the rotor disk. You may.

In this way, the thin-walled plate portion is configured by using the first and second plate portions, and the end portion of the first plate portion is fitted to the second side surface side of the rotor disk to generate centrifugal force. At that time, the second plate portion provided with the thick portion can be elastically deformed.

In order to solve the above problems, the rotary machine according to one aspect of the present invention has the above moving blade body.

According to the present invention, by having the above-mentioned moving blade body, the vibration generated in the moving blade can be stably damped.

According to the present invention, the vibration generated in the moving blade can be stably damped.

It is sectional drawing which shows typically the schematic structure of the rotary machine which concerns on 1st Embodiment of this invention. It is sectional drawing in the _B1-2 line direction of the blade body which comprises the rotary machine shown in _FIG . It is the figure which C-viewed the moving blade body shown in FIG. FIG. 3 is a cross-sectional view of the rotor blade body shown in _FIG . ₃ in the E1 to E2 line directions. It is sectional drawing of the main part of the rotor blade body which concerns on the modification of 1st Embodiment of this invention. It is sectional drawing of the seal member and a rotor disk schematically showing the state which the rotor blade is removed from the rotor disk shown in FIG. It is a figure which saw the moving blade body of the 2nd Embodiment of this invention in the axial direction from the upstream side, and is the figure which shows only a part of the upper part of the moving blade body. FIG. 7 is a cross-sectional view of the rotor blade body shown in _FIG . 7 in the J1 _- J2 line direction. It is an enlarged view of the part surrounded by the region K in the rotor blade body shown in FIG. 8, and is the figure for demonstrating the relationship between the centrifugal force acting on the center of gravity, and the moment by the centrifugal force. It is sectional drawing of the main part of the rotor blade body which concerns on 1st modification of 2nd Embodiment of this invention. It is sectional drawing of the main part of the rotor blade body which concerns on 2nd modification of 2nd Embodiment of this invention.

Hereinafter, embodiments to which the present invention is applied will be described in detail with reference to the drawings.

(First Embodiment)
The schematic configuration of the rotary machine 10 of the first embodiment will be described with reference to FIG. In FIG. 1, the following description will be given by taking a gas turbine as an example of the rotary machine 10. Further, in FIG. 1, a plurality of rotor disks 32 and 47 arranged in the axial direction Da are simplified (in a state where the rotor disks 32 adjacent to each other are not divided and the rotor disks 47 adjacent to each other are not divided). It is shown in a state where they are not divided.

In FIG. 1, A is outside air (hereinafter referred to as “outside air A”), Acom is compressed air (hereinafter referred to as “compressed air Acom”), Ar is the axis of the spindle 20 (hereinafter referred to as “axis Ar”), and Da is. Axial directions (hereinafter referred to as "axis direction Da") are shown respectively.
Further, in FIG. 1, Dau is the upstream side in the axial direction (hereinafter referred to as “Dau on the upstream side in the axial direction”), which is one side of the Da in the axial direction, and Dad is the downstream side in the axial direction (hereinafter referred to as “Dau” on the other side in the axial direction Da). "Dad on the downstream side in the axial direction") and Dc indicate the circumferential direction of the spindle 20 and the rotor disk 47 (hereinafter, referred to as "circumferential direction Dc"), respectively.

Further, in FIG. 1, Dr is the radial direction of the rotor disk 47 (hereinafter, referred to as “diametrical Dr”), and Dr is the radial outer side (hereinafter, “diametrical outer Dr”) which is the side away from the axis Ar in the radial direction Dr. ), Dri indicates the inner side in the radial direction (hereinafter referred to as “inner Dri in the radial direction”) which is the side closer to the axis Ar in the radial direction Dr.

The rotary machine 10 includes a compressor 11, a turbine 13, an intermediate casing 15, a combustor 17, an exhaust chamber 19, and a spindle 20.

The compressor 11 compresses the outside air A to generate compressed air Acom. The compressor 11 has a compressor casing 21 and a compressor rotor 23.

The compressor casing 21 has a cylindrical shape and houses the compressor rotor 23. An air intake port 21A for the compressor 11 to take in the outside air A from the outside is provided on the upstream side of the compressor cabin 21.
A plurality of stationary blade groups 25 are fixed to the radial inner Dri of the compressor casing 21. The plurality of stationary blade groups 25 are arranged at intervals in the axial direction Da. The plurality of stationary blade groups 25 are composed of a plurality of stationary blades 29 arranged in the circumferential direction Dc.

The compressor rotor 23 extends in the Ar direction of the axis line and is arranged outside the main shaft 20 housed in the compressor casing 21.
The compressor rotor 23 rotates about the axis Ar. The compressor rotor 23 has a plurality of rotor disks 32 and a plurality of blade rows 34.
The rotor disk 32 extends in the axial direction Da with the axis Ar as the center. A plurality of rotor disks 32 are arranged at intervals in the axial direction Da. The rotor blade row 34 is fixed to the outer peripheral portion of the rotor disk 32.
Each rotor blade row 34 is arranged on the upstream Dau in the axial direction of any of the stationary blade groups 25. The rotor blade row 34 is composed of a plurality of rotor blades 36 arranged side by side in the circumferential direction Dc.

Next, the turbine 13 will be described with reference to FIGS. 1 to 4. In FIGS. 1 to 4, the same components are designated by the same reference numerals.
In FIG. 4, the shapes of the rotor blade 51 and the rotor disk 47 shown in FIGS. 2 and 3 are shown in a simplified manner.

The turbine 13 is arranged on the Dad on the downstream side in the axial direction of the compressor 11. The turbine 13 has a plurality of blade bodies 40 arranged outside the main shaft 20, a turbine casing 41, and a stationary blade group 44.

The plurality of rotor blades 40 are arranged at intervals with respect to the axial direction Da (see FIG. 1). The rotor blade 40 includes a rotor disk 47, a rotor blade row 49, and a seal member 42 that constitute the turbine rotor 38.
The turbine rotor 38 is provided on the outside of the spindle 20. The turbine rotor 38 has a plurality of rotor disks 47 arranged at intervals with respect to the axial Da, and rotor blade rows 49 provided on each rotor disk 47. The turbine rotor 38 rotates integrally with the main shaft 20 about the axis Ar.

The rotor disk 47 is provided on the outside of the spindle 20. The rotor disk 47 is configured to be rotatable integrally with the spindle 20.
The rotor disk 47 has a second side surface 47a, 47b, an outer peripheral surface 47c, a plurality of fitting grooves 47A, and a first accommodating portion 47B.

The second side surfaces 47a and 47b are surfaces arranged in the axial direction Da. The second side surface 47a is arranged on the upstream side Dau in the axial direction. The second side surface 47b is arranged on the downstream side Dad in the axial direction. The second side surface 47b is a surface arranged on the opposite side of the second side surface 47a.
The outer peripheral surface 47c is a surface facing the platform 52 constituting the rotor blade 51 in the radial direction of the rotor disk 47.

The plurality of fitting grooves 47A are formed on the outer peripheral portion of the rotor disk 47. The plurality of fitting grooves 47A are formed radially so as to be evenly spaced in the circumferential direction Dc.
The plurality of fitting grooves 47A have a shape capable of fitting with the blade root portion 53 of the moving blades 51 constituting the moving blade row 49. The fitting groove 47A is a groove for mounting the moving blade 51.

The first accommodating portion 47B is formed in a portion of the outer peripheral portion of the rotor disk 47 that partitions the outer peripheral surface 47c located on the upstream side Dau in the axial direction, which faces the platform 52. The first accommodating portion 47B is a groove extending in the circumferential direction Dc. A plurality of first accommodating portions 47B are formed in the circumferential direction Dc in a state of being spaced apart from each other.

The first accommodating portion 47B is a groove for accommodating one end portion 42A of the seal member 42. The width W1 of the first accommodating portion 47B in the axial direction Da is configured to be larger than the thickness P1 of one end portion 42A of the sealing member 42.
In this way, by making the width W1 of the first accommodating portion 47B larger than the thickness P1 of one end portion 42A of the seal member 42, one end portion 42A side of the seal member 42 is oriented in the axial direction. It can be transformed into Da.

The rotor disk 47 is formed with a cooling air passage (not shown) through which cooling air passes. The cooling air that has passed through the cooling air passage is introduced into the moving blade 51 and is used for cooling the moving blade 51.

The plurality of blade rows 49 are provided on the outer peripheral portion of each rotor disk 47. As a result, the plurality of blade rows 49 are arranged in the axial direction Da.
The rotor blade row 49 has a plurality of rotor blades 51. The rotor blade 51 has a blade root portion 53, a blade portion 54, and a platform 52.

The wing root portion 53 is provided inside the platform 52. The cross-sectional shape of the wing root portion 53 is a Christmas tree shape (see FIG. 2). The blade root portion 53 is fitted into the fitting groove 47A formed in the rotor disk 47 from the plate thickness direction of the rotor disk 47. As a result, the rotor blade 51 is fixed to the rotor disk 47.

The wing portion 54 is provided on the outside of the platform 52. The blade portions 54 of the plurality of rotor blades 51 constituting the rotor blade row 49 extend radially to the outer Dro in the radial direction.

The platform 52 is a pedestal that connects the wing root portion 53 and the wing portion 54, and is arranged outside the rotor disk 47.
The platform 52 has a pair of gap forming surfaces 52a, first side surfaces 52b and 52c, facing surfaces 52d, and a second accommodating portion 52A.

The pair of gap forming surfaces 52a are surfaces arranged in the circumferential direction Dc. The pair of gap forming surfaces 52a face the gap forming surfaces 52a of other platforms 52 arranged at adjacent positions with the gap H interposed therebetween in the circumferential direction Dc.

The first side surfaces 52b and 52c are surfaces arranged in the axial direction Da. The first side surface 52b is arranged on the upstream side Dau in the axial direction. The first side surface 52b is a surface arranged on the same side as the side on which the second side surface 47a is arranged.
The first side surface 52c is arranged on the downstream side Dad in the axial direction. The first side surface 52c is a surface arranged on the opposite side of the first side surface 52b. The first side surface 52c is arranged on the same side as the side on which the second side surface 47b is arranged.

The facing surface 52d faces the outer peripheral surface 47c of the rotor disk 47 in the radial direction of the rotor disk 47.
A gap I is formed between the facing surface 52d of the platform 52 and the outer peripheral surface 47c of the rotor disk 47.

The second accommodating portion 52A is formed in a portion of the platform 52 that partitions the facing surface 52d located on the upstream side Dau in the axial direction, which faces the first accommodating portion 47B. The second accommodating portion 52A is a groove extending in the circumferential direction Dc.

The second accommodating portion 52A is a groove for accommodating the other end portion 42B of the sealing member 42. The width W2 of the second accommodating portion 52A in the axial direction Da is configured to be larger than the thickness P2 of the other end portion 42B of the sealing member 42.
In this way, by making the width W2 of the second accommodating portion 52A larger than the thickness P2 of the other end portion 42B of the seal member 42, the other end portion 42B side of the seal member 42 is in the axial direction. It can be transformed into Da.

The first and second accommodating portions 47B and 52A described above are accommodating portions for arranging the seal member 42 between the rotor disk 47 and the platform 52.
The depth of the first and second accommodating portions 47B and 52A is set to a depth capable of suppressing the sealing member 42 from coming off from the first and second accommodating portions 47B and 52A when the rotor blade 51 vibrates. ing.

By having the first and second accommodating portions 47B and 52A described above, it is possible to displace one end portion 42A of the seal member 42 in the axial direction Da within the range of the width W1 of the first accommodating portion 47B. At the same time, the other end portion 42B of the seal member 42 can be displaced in the axial direction Da within the range of the width W2 of the second accommodating portion 52A.
As a result, when the rotor blade 51 vibrates, the seal member 42 accommodated in the first and second accommodating portions 47B and 52A can be displaced in the axial direction Da in a deformed state, so that the rotor blade 51 can be displaced. Vibration can be stably damped.

Next, the seal member 42 will be described with reference to FIGS. 3 and 4.
The seal member 42 is a plate-shaped member capable of applying an elastic force in a deformed state. One end 42A of the seal member 42 is housed in the first accommodating portion 47B, and the other end 42B is accommodated in the second accommodating portion 52A.

The seal member 42 is arranged in a deformed state between the rotor disk 47 and the platform 52. That is, the seal member 42 is arranged in a state of being elastically deformed so as to exert an elastic force on the platform 52 in the axial direction Da.
When the seal member 42 is arranged between the rotor disk 47 and the platform 52, the seal member 42 projects to the upstream Dau in the axial direction away from the wing root portion 53.
The seal member 42 closes the axial upstream Dau of the gap I formed between the outer peripheral surface 47c of the rotor disk 47 and the facing surface 52d of the platform 52. As a result, the seal member 42 functions as a seal member that suppresses gas leakage from the gap I.

As the sealing member 42, for example, it is preferable to use a metal plate having excellent heat resistance. As the material of the seal member 42, for example, a Ni-based alloy can be used.
The thickness of the seal member 42 can be made uniform, for example. Further, the thickness of the seal member 42 can be appropriately set according to the usage conditions of the turbine 13, the rotor blade 51, and the rotor disk 47.

By having the seal member 42 having such a configuration, it is possible to always exert the elastic force of the seal member 42 on the moving blade 51. As a result, when vibration is generated in the moving blade 51, the vibration of the moving blade 51 can be stably damped by using the elastic force of the sealing member 42.
That is, the seal member 42 functions not only as a seal member but also as a damping portion that attenuates the vibration of the rotor blade 51.

Referring to FIG. 1, the turbine casing 41 has a cylindrical shape and covers the turbine rotor 38. A plurality of stationary blade groups 44 are fixed to the radial inner Dri of the turbine casing 41. The plurality of stationary blade groups 44 are arranged at intervals in the axial direction Da. Each stationary blade group 44 is composed of a plurality of stationary blades 45 arranged in the circumferential direction Dc.

A cooling air passage through which cooling air passes is formed in the turbine casing 41. The cooling air that has passed through the cooling air passage is introduced into the stationary blade 45 and used for cooling the stationary blade 45.

Depending on the configuration of the stationary blade group 44, the air in the intermediate chassis 15 may be used as cooling air and supplied to the stationary blades 45 constituting the stationary blade group 44 without passing through the cooling air passage in the vehicle interior. be.

A combustion gas flow path 50 formed as an annular space is formed between the radial outer Dro of the rotor disk 47 and the radial inner Dri of the turbine casing 41. The high-temperature combustion gas G generated by the combustor 17 is supplied to the combustion gas flow path 50.

The intermediate casing 15 is arranged between the compressor casing 21 and the turbine casing 41 in the axial direction Da. Compressed air Acom, which is the outside air A compressed by the compressor 11, is introduced into the intermediate vehicle compartment 15.

The combustor 17 is fixed to the intermediate casing 15. A fuel line 55 for supplying fuel F to the combustor 17 is connected to the combustor 17. The fuel line 55 is provided with a fuel control valve 57 for adjusting the fuel flow rate. The combustor 17 produces a high-temperature combustion gas G by burning the fuel F from the fuel supply source in the compressed air Acom.

The exhaust chamber 19 is arranged on the Dad on the downstream side in the axial direction of the turbine casing 41.
The compressor casing 21, the intermediate casing 15, the turbine casing 41, and the exhaust chamber 19 are connected to each other to form the gas turbine casing 58.

According to the rotor blade 40 of the first embodiment, the rotor blade 40 is arranged between the platform 52 and the rotor disk 47 in a state of being elastically deformed so as to have an elastic force in the axial direction Da with respect to the platform 52, and has an axial line. By having the seal member 42 that closes the gap I formed between the outer peripheral surface 47c of the rotor disk 47 and the platform 52 in the direction Da, it is possible to always apply the elastic force of the seal member 42 to the moving blade 51. Become.
As a result, when vibration is generated in the moving blade 51, the vibration of the moving blade 51 can be stably damped by using the elastic force of the sealing member 42.

In the first embodiment, as an example, the first and second accommodating portions 47B and 52A are formed on the Dau on the upstream side in the axial direction of the blade root portion 53, and the seal member is formed on the Dau on the upstream side in the axial direction of the blade root portion 53. Although the case where the 42 is arranged has been described as an example, for example, the first and second accommodating portions 47B and 52A are formed on the axial downstream side Dad of the blade root portion 53, and the axial downstream side of the blade root portion 53 is formed. The seal member 42 may be arranged on the Dad. In this case, the same effect as that of the rotor blade 40 of the first embodiment can be obtained.

Further, in the first embodiment, as an example, the case where the seal member 42 is provided for all the moving blades 51 has been described as an example. However, for example, the seal member 42 of the first embodiment and the seal member 42 have been described. A rotor blade may be formed by combining a sealing member having only a sealing function with a sealing member.

Next, the rotor blade 60 according to the modified example of the first embodiment will be described with reference to FIGS. 5 and 6. In FIG. 5, the same components as those of the structure shown in FIG. 4 are designated by the same reference numerals. In FIG. 5, E is the direction in which the restoring force of the seal member 61 acts (hereinafter referred to as “E direction”), and α is the angle formed by the seal member 61 and the outer peripheral surface 47c of the rotor disk 47 (hereinafter referred to as “angle α”). ) Are shown respectively. In FIG. 6, β indicates an angle formed by the seal member 61 and the outer peripheral surface 47c of the rotor disk 47 (hereinafter, referred to as “angle β”).
Further, in FIG. 6, the same components as those of the structure shown in FIG. 5 are designated by the same reference numerals.

The rotor blade 60 has a first accommodating portion 47C and a second accommodating portion 47C in place of the first accommodating portion 47B, the second accommodating portion 52A, and the seal member 42 constituting the moving blade body 40 of the first embodiment. It is configured in the same manner as the rotor blade 40 except that it has the accommodating portion 52B and the seal member 61.

The first accommodating portion 47C is formed in a portion of the outer peripheral portion of the rotor disk 47 that partitions the outer peripheral surface 47c located on the upstream side Dau in the axial direction, which faces the platform 52. The first accommodating portion 47C is a groove extending in the circumferential direction Dc. The first accommodating portion 47C is inclined in the direction toward the wing root portion 53. One end 61A of the seal member 61 is fitted to the first accommodating portion 47C. As a result, the first accommodating portion 47C accommodates one end portion 61A.

Although not shown in FIGS. 5 and 6, a plurality of first accommodating portions 47C are formed in the circumferential direction of the rotor disk 47 at intervals.

The second accommodating portion 52B is formed in a portion of the platform 52 that partitions the facing surface 52d located on the upstream Dau in the axial direction, in a portion facing the open end of the first accommodating portion 47C.
The second accommodating portion 52B is a groove extending in the circumferential direction of the rotor disk 47. The second accommodating portion 52B is formed so that its depth direction is the same as the direction orthogonal to the facing surface 52d.
The second accommodating portion 52B is fitted with the other end portion 61B of the sealing member 42. As a result, the second accommodating portion 52B accommodates the other end portion 42B.

The seal member 61 is a plate-shaped member that can be elastically deformed. (See FIG. 5). In a state where one end 61A is fitted to the first housing 47C and the other end 61B is not fitted to the second housing 52B (the state shown in FIG. 6), the seal member 61 is , The first accommodating portion 47C extends in the same direction as the extending direction.
As a result, in the state shown in FIG. 6, the seal member 61 is inclined in the direction approaching the wing root portion 53.

In a state where the other end portion 42B is fitted to the second accommodating portion 52B, the seal member 61 extends from the first accommodating portion 47C toward the second accommodating portion 52B and warps. It will have a restoring force that works in the E direction.
At this time, the angle α formed by the outer peripheral surface 47c of the rotor disk 47 and the seal member 61 is closer to 90 ° than the angle β in the state shown in FIG. That is, the other end portion 61B of the seal member 61 is fitted to the second accommodating portion 52B so that the angle of inclination of the seal member 61 with respect to the outer peripheral surface 47c of the rotor disk 47 is large.

According to the moving blade body 60 according to the modification of the first embodiment, the direction toward the blade root portion 53 in a state where one end portion 61A of the seal member 61 is fitted to the first accommodating portion 47C. In a state where the other end portion 61B of the seal member 61 is fitted to the second accommodating portion 52B, the angle of inclination of the seal member 61 with respect to the outer peripheral surface 47c of the rotor disk 47 becomes large. The other end 61B of the seal member 61 is fitted to the accommodating portion 52B of 2.

With such a configuration, the restoring force of the seal member 61 (the seal member 61 tilts toward the blade root portion 53) with the seal member 61 fitted to the first and second accommodating portions 47C and 52B. The force (force to return to the original inclined state) is always applied to the rotor blade 51.
As a result, when the moving blade 51 vibrates, the vibration of the moving blade 51 can be stably damped by the restoring force of the seal member 61.

(Second embodiment)
The rotor blade 70 according to the second embodiment will be described with reference to FIGS. 7 to 9. In FIG. 7, the same components as those of the structure shown in FIG. 3 are designated by the same reference numerals. In FIG. 8, the same components as those of the structures shown in FIGS. 4 and 7 are designated by the same reference numerals. In FIG. 9, the same components as those of the structure shown in FIG. 8 are designated by the same reference numerals.
In FIG. 9, N is the center of gravity of the seal member 71 (hereinafter referred to as “center of gravity”), Cf is a centrifugal force (hereinafter referred to as “centrifugal force Cf”), and M1 is a first moment generated by the centrifugal force Cf (hereinafter referred to as “centrifugal force Cf”). “First moment M1”) and M2 indicate a second moment generated by centrifugal force Cf (hereinafter referred to as “second moment M2”), respectively.

The rotor blade body 70 has a seal member 71 instead of the seal member 42 constituting the rotor blade body 40 of the first embodiment, and the second side surface 47a and the first side surface 52b are arranged in the axial direction Da. It is configured in the same manner as the rotor blade 40 except that it is arranged on a virtual plane orthogonal to the blade.

The seal member 71 has a thin-walled plate portion 73 and a thick-walled portion 75.
The thin-walled plate portion 73 is a plate-shaped member that extends outward in the radial direction of the rotor disk 47 and is elastically deformable in the axial direction Da. The thin plate portion 73 has surfaces 73a and 73b arranged in the axial direction Da. The surface 73a is a surface arranged on the moving blade 51 side.
The surface 73a has a portion that comes into contact with the second side surface 47a and a portion that comes into contact with the first side surface 52b of the platform 52.

The thin plate portion 73 that partitions the surface 73a is joined to the rotor disk 47 that partitions the second side surface 47a. As a result, the position of the portion of the thin-walled plate portion 73 joined to the rotor disk 47 is regulated by the rotor disk 47. The position of D shown in FIG. 9 is the fixed end (hereinafter referred to as “fixed end D”).
The surface 73b is a surface arranged on the opposite side of the surface 73a.

The thin-walled plate portion 73 having the above configuration is arranged so that the end portion of the circumferential direction Dc overlaps with the end portion of another thin-walled plate portion 73 arranged in the circumferential direction Dc (see FIG. 7).

Since the first side surface 52b of the platform 52 and the thin-walled plate portion 73 are not fixed, the thin-walled plate portion 73 located radially outside the fixed end D is in a state of being elastically deformable. ing.

The thick portion 75 is provided on the surface 73b facing the platform 52 in the axial direction Da. The thick portion 75 is configured so that the thickness in the axial direction Da is thicker than the thickness of the thin plate portion 73.
In this way, by providing the thick portion 75 which is thicker than the thin plate portion 73 on the surface 73b of the thin plate portion 73 facing the platform 52, the position of the center of gravity N of the seal member 71 is set to the thick portion. It can be arranged within 75.

The seal member 71 having the above configuration closes the axial upstream Dau of the gap I formed between the outer peripheral surface 47c of the rotor disk 47 and the facing surface 52d of the platform 52.

In the rotor blade 70 having such a configuration, when the rotor disk 47 rotates, a centrifugal force Cf (a force acting on the radial outer side of the rotor disk 47) is applied to the center of gravity N of the seal member 71.
In this way, when centrifugal force is applied to the center of gravity N (point of action), the first moment M1 and the first moment M1 acting in the direction connecting the fixed end D and the center of gravity N act on the center of gravity N. A second moment M2 that acts in a direction orthogonal to the direction and in a direction toward the moving blade 51 (platform 52) is generated.
Therefore, according to the rotor blade 70 of the second embodiment, when the rotor blade 51 vibrates during the rotation of the rotor disk 47, the vibration of the rotor blade 51 is stably damped by the second moment M2. be able to.

In the second embodiment, as an example, the case where the seal member 71 is arranged on the Dau on the upstream side in the axial direction of the wing root portion 53 has been described as an example. The seal member 71 may be arranged in the. In this case, the same effect as that of the rotor blade 70 of the second embodiment can be obtained.

Further, in the second embodiment, the same material may be used for the thin-walled plate portion 73 and the thick-walled portion 75, or different materials may be used.
Further, in the second embodiment, as an example, the case where the seal member 81 and the rotor disk 47 are separate bodies has been described as an example, but the seal member 81 and the rotor disk 47 may be integrally formed.

Next, with reference to FIG. 10, the rotor blade 80 according to the first modification of the second embodiment will be described. In FIG. 10, the same components as those of the structure shown in FIG. 8 are designated by the same reference numerals.

The rotor blade 80 has a seal member 81 in place of the seal member 71 constituting the rotor blade 70 of the second embodiment, and is moving except that a fitting groove 47D is further formed in the rotor disk 47. It is configured in the same manner as the blade body 70.

The fitting groove 47D is located on the upstream side Dau in the axial direction and is formed on the rotor disk 47 constituting the second side surface 47a. As a result, the fitting groove 47D is exposed on the second side surface 47a. The fitting groove 47D is a groove extending in the axial direction Da.

The seal member 81 is configured in the same manner as the seal member 71 except that it has the thin-walled plate portion 83 instead of the thin-walled plate portion 73 constituting the seal member 71 of the second embodiment.
The thin-walled plate portion 83 has a first plate portion 84 and a second plate portion 85.
The first plate portion 84 is a plate portion extending in the axial direction Da. One end of the first plate portion 84 is fitted into the fitting groove 47D of the rotor disk 47.

The second plate portion 85 is integrally formed with the other end portion of the first plate portion and extends radially outward of the rotor disk 47. The second plate portion 85 is in contact with the first side surface 52b and the second side surface 47a.

The rotor blade 80 according to the first modification of the second embodiment having such a configuration can obtain the same effect as the rotor blade 70 of the second embodiment described above.

Next, with reference to FIG. 11, the rotor blade 90 according to the second modification of the second embodiment will be described. In FIG. 10, the same components as those of the structure shown in FIG. 8 are designated by the same reference numerals.

In the rotor blade body 90 according to the second modification of the second embodiment, the position of the second side surface 47a in the axial direction Da is arranged closer to the blade root portion 53 than the position of the first side surface 52b, and the rotor disk is It is configured in the same manner as the rotor blade 80 except that a gap 91 is formed between the 47 and the first plate portion 84.
With such a configuration, the first plate portion 84 can be moved not only to the Dad on the upstream side in the axial direction but also to the Dad on the downstream side in the axial direction.

The rotor blade 90 according to the second modification of the second embodiment having the above configuration can obtain the same effect as the rotor blade 70 of the second embodiment described above.

In the first modification and the second modification of the second embodiment, as an example, a case where the seal member 81 is arranged on the Dau on the upstream side in the axial direction of the blade root portion 53 has been described as an example. , The seal member 81 may be arranged on the Dad on the downstream side in the axial direction of the blade root portion 53.

Although the preferred embodiments of the present invention have been described in detail above, the present invention is not limited to such specific embodiments, and various aspects of the present invention are described within the scope of the claims. It can be transformed and changed.

10 ... Rotating machine 11 ... Compressor 13 ... Turbine 15 ... Intermediate casing 17 ... Combustor 19 ... Exhaust chamber 20 ... Main shaft 21 ... Compressor chassis 21A ... Air intake port 23 ... Compressor rotor 25, 44 ... Static blade group 29,45 ... Static wing 32,47 ... Rotor disk 34,49 ... Moving wing train 36,51 ... Moving wing 38 ... Turbine rotor 40,60,70,80,90 ... Moving wing body 41 ... Turbine cabin 42,61 , 71, 81 ... Seal members 42A, 61A ... One end 42B, 61B ... The other end 47a, 47b ... Second side surface 47A, 47D ... Fitting groove 47B, 47C ... First accommodating portion 47c ... Outer circumference Surface 50 ... Combustion gas flow path 52 ... Platform 52a ... Gap forming surface 52A, 52B ... Second accommodating portion 52b, 52c ... First side surface 52d ... Opposing surface 53 ... Wing root 54 ... Wing 55 ... Fuel line 57 ... Fuel control valve 73, 83 ... Thin-walled plate 73a, 73b ... Surface 75 ... Thick-walled 84 ... First plate 85 ... Second plate 91, H, I ... Gap A ... Outside air Acom ... Compressed air Ar ... Axial line Cf ... Centrifugal force D ... Fixed end Da ... Axial direction Dau ... Axial direction upstream side Dad ... Axial direction downstream side Dc ... Circumferential direction Dr ... Radial direction Dr ... Radial direction outer side Dri ... Electrical direction inner side F ... Fuel G ... Combustion gas K ... Region M1, M2 ... Moment N ... Center of gravity P1, P2 ... Thickness Q ... Direction W1, W2 ... Width α, β ... Angle

Claims (8)

A rotor disk with multiple fitting grooves formed on the outer circumference and rotatable integrally with the spindle,
A wing portion, a wing root portion fitted in the fitting groove, and a plurality of moving blades arranged between the wing portion and the wing root portion and having a platform facing the outer peripheral surface of the rotor disk.
A sealing member that closes a gap formed between the outer peripheral surface of the rotor disk and the platform in the axial direction of the main axis.
Equipped with
The sealing member is curved so as to be convex in a direction away from the rotor disk and the platform so that elastic force can be applied to the platform, and the platform and the rotor are elastically deformed. Placed between the disc and
A first accommodating portion in which one end of the sealing member is accommodated is formed on the outer peripheral portion of the rotor disk.
A second accommodating portion in which the other end of the sealing member is accommodated is formed in a portion of the platform facing the first accommodating portion.
The sealing member is fixed from the radial inside by the first accommodating portion and is fixed from the radial outside by the second accommodating portion . The width of the first accommodating portion in the axial direction is configured to be larger than the thickness of the one end portion of the sealing member.
The width of the second accommodating portion in the axial direction is configured to be larger than the thickness of the other end portion of the sealing member.
The rotor blade body according to claim 1 , wherein the seal member is arranged in the first and second accommodating portions in a state of being deformed in the axial direction. The seal member is inclined in a direction approaching the wing root portion in a state where one end thereof is fitted to the first accommodating portion.
The rotor blade body according to claim 1 , wherein the other end portion of the seal member is fitted to the second accommodating portion so that the angle of inclination of the seal member with respect to the outer peripheral surface of the rotor disk is large. .. A rotor disk with multiple fitting grooves formed on the outer circumference and rotatable integrally with the spindle,
A wing portion, a wing root portion fitted in the fitting groove, and a plurality of moving blades arranged between the wing portion and the wing root portion and having a platform facing the outer peripheral surface of the rotor disk.
A sealing member that closes a gap formed between the outer peripheral surface of the rotor disk and the platform in the axial direction of the main axis.
Equipped with
The platform has a first side surface arranged in the axial direction.
The rotor disk has a second side surface arranged on the same side as the first side surface in the axial direction.
The sealing member extends outward in the radial direction of the rotor disk, has a plate shape that can be elastically deformed in the axial direction, is brought into contact with the first side surface, and its position is restricted by the rotor disk. Of the surface of the end portion of the thin-walled plate portion that is in contact with the first side surface and the thin-walled plate portion that is fixed at the above, the surface is provided on the surface located on the opposite side of the surface that contacts the first side surface. It has a thick portion that is thicker than the thin plate portion in the axial direction and has a free end because it can be attached to and detached from the first side surface.
The thin-walled plate portion is a rotor blade body that is arranged with a gap in the axial direction with respect to the rotor disk. The rotor blade body according to claim 4 , wherein the thin plate portion is fixed to the second side surface of the rotor disk. The rotor blade body according to claim 4 , wherein the seal member is integrally formed with the rotor disk. The thin-walled plate portion is integrally formed with the first plate portion extending in the axial direction and the first plate portion, extends outward in the radial direction of the rotor disk, and is in contact with the first side surface. It has 2 plates and
The rotor blade body according to claim 4 , wherein the end portion of the first plate portion is fitted to the second side surface side of the rotor disk. A rotary machine having a rotor blade according to any one of claims 1 to 7 .

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