JP6990122B2 - 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 suppress the leakage of combustion gas from the gap formed between the platforms of the plurality of rotor blades, and at the resonance point passed at the start of the rotating machine, the rotor blades. It is necessary to attenuate the vibration of the.

Patent Document 1 includes a damper member mounted in a gap between platforms adjacent to each other in the circumferential direction, and an adjusting member interposed between the platform and the damper member and capable of adjusting the contact angle with respect to the damper member. The blade body is disclosed.

Japanese Unexamined Patent Publication No. 2014-185646

In recent years, it has been desired to appropriately suppress the vibration generated in the rotor blades and to reduce the variation in the frequency and damping according to the rotation speed of the rotor disk.

Therefore, the present invention provides a rotor blade and a rotary machine capable of appropriately suppressing the vibration generated in the rotor blade and reducing the variation in the frequency and damping according to the rotation speed of the rotor disk. The purpose is to provide.

In order to solve the above problems, the rotor blades according to one aspect of the present invention include a rotor disk that can rotate integrally with the main shaft, and a plurality of rotor blades that are mounted on the rotor disk and extend radially from the outer peripheral portion of the rotor disk. The rotor blades are provided with a damper member that comes into contact with the facing surfaces of a pair of rotor blades arranged adjacent to each other in the circumferential direction of the rotor blade, and the damper member is such that the rotor disk rotates. The gap formed between the platforms of the pair of rotor blades is closed, and the contact area of the pair of rotor blades with the facing surface of the platform is changed according to the rotation speed of the rotor disk. The member increases the contact area of the pair of rotor blades with the facing surfaces of the platform when the rotation speed of the rotor disk is the first rotation speed, and the rotation speed of the rotor disk is the first rotation speed. At a second rotation speed different from that, the contact area of the pair of rotor blades with the facing surface of the platform is reduced, and the facing surface of the pair of rotor blades is from the blade portion of the rotor blade to the rotor disk. The damper member has an inclined surface that expands the diameter of the space formed between the platforms of the pair of rotor blades, and the damper member has a chevron shape along the facing surface of the pair of rotor blades. It is a plate-shaped damper and has a plurality of inclined portions whose width increases outward from the center position of the damper member, and the inclination angles of the plurality of inclined portions are outward from the center position of the damper member. It gets bigger as it gets bigger.

According to the present invention, by having the damper member that closes the gap formed between the platforms of the pair of rotor blades, it is possible to prevent the combustion gas from leaking to the rotor disk side through the gap.
Further, it is possible to generate a large frictional resistance by increasing the area between the facing surface of the platform of the pair of rotor blades and the damper member at the rotation number at which resonance occurs at the time of starting. As a result, the vibration generated in the rotor blade can be appropriately suppressed according to the rotation speed of the rotor disk (the rotation speed at which resonance occurs).

Further, at a rotation speed at which resonance does not occur, the frictional resistance can be reduced by reducing the area between the facing surface of the platform of the pair of rotor blades and the damper member. This makes it possible to reduce variations in frequency and damping during rated operation.
Further, when the rotation speed of the rotor disk is the first rotation speed, the damper member that increases the contact area between the facing surfaces of the platform of the pair of rotor blades is provided, so that the rotation speed is the first rotation speed. When resonance occurs, the vibration generated in the moving blade can be appropriately suppressed.
Further, by having a damper member that reduces the contact area of the pair of rotor blades with the facing surface at the second rotation speed, the platform of the pair of rotor blades has a damper member at the second rotation speed. It is possible to reduce the frictional resistance generated between the facing surface and the damper member. This makes it possible to reduce variations in frequency and attenuation.
A plurality of inclined portions having a mountain-shaped shape along the facing surfaces of the pair of rotor blades, the width increases from the center position toward the outside, and the inclination angle increases from the center position of the damper member toward the outside. By having it, when the rotation speed of the rotor disk is low (when the rotation speed at which resonance occurs), the outside of the damper member is formed, and the wide inclined portion and the facing surface of the pair of rotor blades are brought into contact with each other. It becomes possible.
As a result, it is possible to generate a large frictional resistance between the facing surfaces of the pair of rotor blades and the damper member, so that the vibration generated in the rotor blades can be appropriately suppressed.

Further, in the rotor blade body according to one aspect of the present invention, the plurality of inclined portions each have a plurality of contact portions arranged in a direction in which the main shaft extends, and the plurality of contact portions are the pair. It may have a contact surface in contact with the facing surface of the moving blade.

As described above, the plurality of contact portions arranged in the direction in which the spindle extends have contact surfaces that come into contact with the facing surfaces of the pair of rotor blades, so that the tilted portions that form the outside of the damper member among the plurality of inclined portions are inclined. It is possible to make the contact area where the portion and the facing surface of the pair of rotor blades contact and the contact area where the inclined portion arranged in the center of the damper member and the facing surface of the pair of rotor blades contact differently. Will be. This makes it possible to adjust the frictional resistance generated when the facing surfaces of the pair of rotor blades come into contact with the damper member.

Further, in the moving blade body according to one aspect of the present invention, among the platforms of the pair of moving blades, the contact portion of one of the platforms that comes into contact with the damper member when the rotation speed of the rotor disk is high is described as described above. The damper member may be fixed.

In this way, by fixing the contact portion of one of the platforms of the pair of rotor blades that comes into contact with the damper member when the rotation speed of the rotor disk is high and the damper member, the facing surfaces of the pair of rotor blades are opposed to each other. It is possible to maintain the posture of the damper member with respect to the target. As a result, the facing surfaces of the pair of rotor blades and the damper member can be brought into contact with each other in an appropriate state.

Further, the rotor blades according to one aspect of the present invention include a rotor disk that can rotate integrally with the main shaft, and a plurality of rotor blades that are mounted on the rotor disk and extend radially from the outer peripheral portion of the rotor disk. A damper member that comes into contact with the facing surfaces of a pair of rotor blade platforms arranged adjacent to each other in the circumferential direction of the rotor disk is provided, and the damper member comprises the pair of damper members when the rotor disk rotates. The gap formed between the platforms of the moving blades is closed, the contact area of the pair of moving blades with the facing surface of the platform is changed according to the rotation speed of the rotor disk, and the facing surfaces of the pair of moving blades are changed. The space formed on the platform of the pair of rotor blades is an inclined surface that expands in diameter from the blade portion of the pair of rotor blades toward the rotor disk, and the damper member is the pair of rotor blades. It has a mountain-shaped shape along the facing surfaces of the rotor blades, and is provided at both ends of the mountain-shaped portions that come into contact with the facing surfaces of the pair of rotor blades when the rotation speed of the rotor disk is high and the mountain-shaped portions in the circumferential direction. It has a bent portion including an end surface that comes into contact with the facing surfaces of the pair of rotor blades at a stage where the rotation speed of the rotor disk is low .

In this way, the mountain shape is formed along the facing surfaces of the pair of rotor blades, and the mountain-shaped portion that comes into contact with the facing surfaces of the pair of rotor blades when the rotation speed of the rotor disk is high, and the mountain-shaped portion in the circumferential direction. The damper member has a bent portion provided at both ends and including end faces that come into contact with the facing surfaces of the pair of rotor blades at a stage where the rotation speed of the rotor disk is low, so that resonance occurs when the rotation speed of the rotor disk is high. When it occurs, it is possible to increase the contact area between the facing surfaces of the pair of rotor blades and the damper member.
This makes it possible to generate a large frictional resistance between the facing surface of the pair of rotor blades and the mountain-shaped portion when the rotation speed of the rotor disk is high, so that the vibration generated in the rotor blades can be properly generated. It can be suppressed.

Further, in the rotor blade body according to one aspect of the present invention, one of the bent portions provided at both ends of the mountain-shaped portion may be fixed to the end surface of the bent portion and the platform.

In this way, by fixing the end face and the facing surface of one of the bent portions provided at both ends of the mountain-shaped portion, the posture of the damper member with respect to the facing surfaces of the pair of rotor blades can be maintained. It will be possible. As a result, the facing surfaces of the pair of rotor blades and the damper member can be brought into contact with each other in an appropriate state.

Further, in the moving blade body according to one aspect of the present invention, one end of the facing surfaces of the pair of moving blades is fixed to the facing surface, and the moving blade body has a support member that maintains the posture of the damper member. May be good.

In this way, by having a support member whose one end is fixed to one of the facing surfaces of the pair of rotor blades and which maintains the posture of the damper member, the pair of moving blades moves in a state where the rotor disk is not rotating. It is possible to prevent the facing surface of the blade from being significantly separated from the damper member.
Further, it is possible to make the contact surface of the damper member and the facing surface of the pair of moving blades face each other in a state where the rotor disk is not rotating. As a result, when the rotor disk is rotated, the facing surfaces of the pair of rotor blades and the damper member can be brought into contact with each other in an appropriate state.

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, it is possible to appropriately suppress the vibration generated in the moving blade.

According to the present invention, it is possible to appropriately suppress the vibration generated in the moving blade and reduce the variation in frequency and damping.

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 a perspective view of the moving blade shown in FIG. It is an enlarged sectional view of the damper member of 1st Embodiment shown in FIG. It is a figure which D-viewed the damper member shown in FIG. FIG. 2 is a cross-sectional view corresponding to a portion of the structure shown in FIG. 2 surrounded by the region C, and a contact state between the facing surfaces of the pair of rotor blades and the damper member when the rotor disk is rotating at a low speed. It is a figure which shows schematically. FIG. 2 is a cross-sectional view corresponding to a portion of the structure shown in FIG. 2 surrounded by the region C, and contact between the facing surfaces of the pair of rotor blades and the damper member when the rotor disk is rotating at a medium speed. It is a figure which shows the state schematically. It is a cross-sectional view corresponding to the portion of the structure shown in FIG. 2 surrounded by the region C, and the contact state between the facing surface of the pair of rotor blades and the damper member when the rotor disk is rotating at high speed. It is a figure which shows schematically. It is an enlarged sectional view of the main part of the moving blade body which concerns on the 1st modification of 1st Embodiment of this invention, and the facing surface and a damper of a pair of moving blades when a rotor disk is rotating at a low speed. It is a figure which shows typically the contact state with a member. It is an enlarged sectional view of the main part of the moving blade body which concerns on the 2nd modification of 1st Embodiment of this invention, and the facing surface and a damper of a pair of moving blades when a rotor disk is rotating at a low speed. It is a figure which shows typically the contact state with a member. It is a top view of the damper member which concerns on the modification of 1st Embodiment. It is a figure which shows the cross section of the damper member shown in FIG. 11 in the E ₁ -E ₂ line direction, and is It is a sectional view. _FIG . 11 is a view showing a cross section of the damper member in the F1 to F2 line direction, and _a rotor blade body schematically showing a contact state between the facing surfaces of the pair of rotor blades and the damper member during high-speed rotation. It is a sectional view. It is an enlarged sectional view of the main part of the moving blade body which concerns on 2nd Embodiment of this invention, and the contact state between the facing surface of a pair of moving blades and a damper member when a rotor disk is rotating at a low speed. It is a figure which shows schematically. It is an enlarged sectional view of the main part of the moving blade body which concerns on 2nd Embodiment of this invention, and the contact state between the facing surface of a pair of moving blades and a damper member when a rotor disk is rotating at a high speed. It is a figure which shows schematically. FIG. 6 is an enlarged cross-sectional view of the damper member shown in FIG.

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 a radial direction with respect to the axis Ar (hereinafter, referred to as “diametrical Dr”), and Dr is a radial outer side (hereinafter, “diametrical outer Dr”) which is a side away from the axis Ar in the radial direction Dr. ) And Dri indicate 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 5. In FIGS. 1 to 5, the same components are designated by the same reference numerals.

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 body 40 has a rotor disk 47 and a rotor blade row 49 constituting the turbine rotor 38, and a damper member 42.
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.

A 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 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. The shape of the platform 52 is a curved plate shape.

Two blades 51 (hereinafter, "a pair of blades") arranged at positions adjacent to each other in the circumferential direction Dc in a state where a plurality of blades 51 constituting the blade row 49 are fitted in the fitting grooves 47A, respectively. A gap H is formed between the platforms 52 of the blades 51).
If the combustion gas G (see FIG. 1) flowing outside the plurality of platforms 52 leaks to the rotor disk 47 side through the gap H, the turbine efficiency is lowered, which is not preferable.

The platform 52 has a gap forming surface 52a for partitioning the gap H and a facing surface 52b. The gap forming surface 52a and the facing surface 52b are arranged in the circumferential direction Dc.
The facing surface 52b is arranged between the gap forming surface 52a and the blade root portion 53. The facing surfaces 52b of the pair of rotor blades 51 are inclined surfaces that expand the space formed between the platforms 52 of the pair of rotor blades 51 toward the rotor disk 47 from the blade portions 54 of the rotor blades 51. ..

Next, the damper member 42 will be described with reference to FIGS. 1, 2, and 4 to 8.
In FIG. 4, T is the apex of the damper member 42 (hereinafter referred to as “vertex T”), O is the axis of symmetry (hereinafter referred to as “axis of symmetry O”), Vp1 passes through the axis of symmetry O, and the damper member 42 is bisected by 2. The virtual planes that are equally divided (hereinafter referred to as "first virtual plane Vp1") are shown.
The axis of symmetry O is also a line connecting the center positions of the damper member 42.

Further, in FIG. 4, Vp2 passes through the apex T, a virtual plane orthogonal to the first virtual plane Vp1 (hereinafter referred to as “second virtual plane Vp2”), and α is the first inclined portion 56. The inclination angle formed by the contact surface 56a and the second virtual plane Vp2 (hereinafter referred to as “inclination angle α”), β is the inclination formed by the contact surface 57a of the second inclined portion 57 and the second virtual plane Vp2. The angles (hereinafter referred to as "tilt angle β") are shown respectively.
Further, in FIG. 4, W1 indicates the width of the first inclined portion 56 (hereinafter referred to as “width W1”), and W2 indicates the width of the second inclined portion 57 (hereinafter referred to as “width W2”). .. In FIG. 4, the same components as those of the structure shown in FIG. 2 are designated by the same reference numerals.

In FIG. 5, the same components as those of the structure shown in FIG. 4 are designated by the same reference numerals. In FIGS. 6 to 8, the same components as those of the structures shown in FIGS. 2 and 4 are designated by the same reference numerals.

The damper member 42 is provided between the facing surfaces 52b of the pair of rotor blades 51 and the rotor disk 47. The damper member 42 has a symmetrical shape with the axis of symmetry O interposed therebetween. The damper member 42 is a plate-shaped damper having a mountain shape along the facing surfaces 52b of the pair of moving blades 51.
The damper member 42 has a pair of first inclined portions 56 and a pair of second inclined portions 57. That is, the damper member 42 is composed of a plurality of inclined portions (in the case of the first embodiment, a pair of first and second inclined portions 56, 57).

The pair of first inclined portions 56 are arranged so as to sandwich the axis of symmetry O and are integrally configured. The pair of first inclined portions 56 constitutes the central portion of the damper member 42. The pair of first inclined portions 56 has an open end of a gap H located on the rotor disk 47 side, and a contact surface 56a facing a part of the facing surfaces 52b of the pair of rotor blades 51. The contact surface 56a is inclined at an inclination angle α with respect to the second virtual plane Vp2.

The pair of first inclined portions 56 functions as a sealing member that closes the open end of the gap H located on the rotor disk 47 side while the rotor disk 47 is rotating. As a result, it is possible to prevent the combustion gas from leaking to the rotor disk 47 side through the gap H.

The contact surface 56a comes into contact with a part of the facing surfaces 52b of the pair of rotor blades 51 when the rotor disk 47 rotates at a medium speed (see FIG. 7).
Further, the contact surface 56a comes into contact with a corner portion formed between the gap forming surface 52a and the facing surface 52b when the rotor disk 47 rotates at a high speed (an example of a second rotation speed) (see FIG. 8). ).

Of the platforms 52 of the pair of rotor blades 51, the corner portion formed between the gap forming surface 52a and the facing surface 52b of one platform 52 and the contact surface 56a may be fixed. That is, of the platforms 52 of the pair of moving blades 51, the contact portion of one of the platforms 52 that comes into contact with the damper member 42 when the rotation speed of the rotor disk 47 is high may be fixed to the damper member 42.

In this way, by fixing the corner portion formed between the gap forming surface 52a and the facing surface 52b of one platform 52 and the contact surface 56a, the damper member 42 with respect to the facing surface 52b of the pair of moving blades 51 It is possible to maintain the posture of.
As a result, the facing surfaces 52b of the pair of rotor blades 51 and the damper member 42 can be brought into contact with each other in an appropriate state (specifically, the facing surfaces 52b are brought into contact with the contact surface 56a or the contact surface 57a).

The pair of second inclined portions 57 are provided on both sides of the pair of first inclined portions 56 so as to sandwich the pair of first inclined portions 56. The pair of second inclined portions 57 constitutes the outside of the damper member 42. The pair of second inclined portions 57 is formed integrally with the pair of first inclined portions 56. The width W2 of the second inclined portion 57 is configured to be larger than the width W1 of the first inclined portion 56.

The pair of second inclined portions 57 has a contact surface 57a facing the facing surface 52b. The contact surface 57a is inclined at an inclination angle β with respect to the second virtual plane Vp2. The tilt angle β is set to be larger than the tilt angle α.

As described above, the rotor disk 47 is provided with the pair of second inclined portions 57 that are inclined at the inclination angle β larger than the inclination angle α on the outside of the pair of the first inclined portions 56 having the inclination angle α. When the blades rotate at a low speed, the facing surfaces 52b of the pair of rotor blades 51 and the entire contact surface 57a can be brought into contact with each other while the facing surfaces 52b of the pair of rotor blades 51 and the contact surface 56a are separated from each other. (See FIG. 6).
As a result, when resonance occurs when the rotation speed of the rotor disk 47 is low (an example of the first rotation speed), the vibration generated in the rotor blade 51 can be appropriately suppressed.

The contact area when the facing surfaces 52b of the pair of rotor blades 51 and the entire contact surface 57a come into contact with each other during low-speed rotation of the rotor disk 47 is the contact area of the pair of rotor blades 51 facing each other during medium-speed rotation of the rotor disk 47. It is larger than the contact area when the surface 52b and a part of the contact surface 56a are in contact with each other.
Therefore, the frictional resistance generated between the facing surface 52b and the contact surface 57a is larger than the frictional resistance generated between the facing surface 52b and the contact surface 56a.

As described above, the damper member 42 increases the contact area of the pair of rotor blades 51 with the facing surface 52b of the platform 52 when the rotation speed of the rotor disk 47 is low, and faces each other as the rotation speed of the rotor disk increases. The contact area with the surface 52b is reduced.

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 59 that regulates 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 has a damper member 42 that increases the contact area of the pair of rotor blades 51 with the facing surface 52b when the rotation speed of the rotor disk 47 is low. When resonance occurs when the rotation speed of the disk 47 is low, the vibration generated in the rotor blade 51 can be appropriately suppressed.

Further, as the rotation speed of the rotor disk 47 of the damper member 42 increases, the contact area of the pair of rotor blades 51 with the facing surface 52b is reduced, so that the facing surfaces of the pair of rotor blades 51 at the second rotation speed are reduced. It is possible to reduce the frictional resistance generated between the 52b and the damper member 42. This makes it possible to reduce variations in frequency and attenuation.

Further, the rotary machine 10 having the rotor blade 40 having the above configuration can appropriately suppress the vibration generated in the rotor blade 51 at the time of low-speed rotation in which resonance occurs (an example of the first rotation speed). can.

In the first embodiment, as an example, a case where the damper member 42 is configured by using a pair of first and second inclined portions 56, 57 (that is, two types of inclined portions) will be described as an example. However, for example, an inclined portion having a contact surface inclined more than the inclination angle β may be provided on the outside of the second inclined portion 57.

That is, the damper member 42 is composed of two or more types of inclined portions whose width increases toward the outside from the center position of the damper member 42, and the inclination angles of the plurality of inclined portions increase toward the outside from the center position. It may be configured as follows.
With such a configuration, even if a resonance point exists when the rotation speed of the rotor disk 47 is considerably low, the contact resistance at the resonance point can be increased, which is generated in the rotor blade 51. Vibration can be suppressed appropriately.

Next, with reference to FIG. 9, the rotor blade 60 according to the first modification of the first embodiment of the present invention will be described. In FIG. 9, the same components as those of the structure shown in FIG. 6 are designated by the same reference numerals.

The rotor blade body 60 is configured in the same manner as the rotor blade body 40 (see FIG. 6) described in the first embodiment, except that the rotor blade body 60 has a support member 61.
The support member 61 is a member that supports the damper member 42 in a state where the rotor disk 47 is not rotating. One end 61A of the support member 61 is fixed to one facing surface 52b. The other end 61B of the support member 61 is not fixed to the other facing surface 52b.

The support member 61 is arranged so as to face the surface 42a (the surface arranged on the opposite side of the contact surfaces 56a and 57a) of the damper member 42.
The support member 61 has a support surface 61a that faces the surface 42a of the damper member 42 and has a shape that follows the shape of the surface 42a.

According to the rotor blade 60 according to the first modification of the first embodiment, by having the support member 61 having the above configuration, the contact surface of the damper member 42 is in a state where the rotor disk 47 is not rotating. It is possible to face the 56a and 57a with the facing surfaces 52b of the pair of rotor blades 51.
As a result, during low-speed rotation of the rotor disk 47 where resonance occurs, the facing surfaces 52b of the pair of rotor blades 51 and the contact surface 57a of the damper member 42 are brought into contact with each other in an appropriate state to generate a large frictional resistance. Therefore, the vibration generated in the moving blade 51 can be appropriately suppressed.
Further, by reducing the area between the facing surface 52b of the pair of rotor blades 51 and the damper member 42 at the rotation speed at which resonance does not occur, it is possible to reduce the variation in the frequency and damping of the rotor blades 51. ..

Next, with reference to FIG. 10, the rotor blade 65 according to the second modification of the first embodiment of the present invention will be described. In FIG. 10, the same components as those of the structure shown in FIG. 6 are designated by the same reference numerals.

The rotor blade body 65 is configured in the same manner as the rotor blade body 40 (see FIGS. 4 and 5) described in the first embodiment, except that the rotor blade body 65 has a support member 66.
The support member 66 is a member that supports the damper member 42 in a state where the rotor disk 47 is not rotating. One end 66A of the support member 66 is fixed to one facing surface 52b. The other end 66B of the support member 61 is not fixed to the other facing surface 52b.

The support member 66 has a support surface 66a facing the surface 42a of the damper member 42. The support surface 66a is a flat surface. The support surface 66a supports the surface 42a side of the damper member 42 in a state where the rotor disk 47 is not rotating.

According to the moving blade body 65 according to the second modification of the first embodiment, one end 66A is fixed to one of the facing surfaces 52b of the facing surfaces 52b of the pair of moving blades 51, and the posture of the damper member 42 is changed. By having the supporting member 66 to be maintained, it is possible to prevent the facing surfaces 52b of the pair of rotor blades 51 and the damper member 42 from being significantly separated from each other when the rotor disk 47 is not rotating.

Further, in a state where the rotor disk 47 is not rotating, the contact surfaces 56a and 57a of the damper member 42 and the facing surfaces 52b of the pair of rotor blades 51 can face each other.
As a result, during low-speed rotation of the rotor disk 47 where resonance occurs, the facing surfaces 52b of the pair of rotor blades 51 and the contact surface 57a of the damper member 42 are brought into contact with each other in an appropriate state to generate a large frictional resistance. Therefore, the vibration generated in the moving blade 51 can be appropriately suppressed.
Further, by reducing the area between the facing surface 52b of the pair of rotor blades 51 and the damper member 42 at the rotation speed at which resonance does not occur, it is possible to reduce the variation in the frequency and damping of the rotor blades 51. ..

Next, the rotor blade 70 according to the third modification of the first embodiment will be described with reference to FIGS. 11 to 13. In FIGS. 12 and 13, the same components as those of the structures shown in FIGS. 4 to 6 and 11 are designated by the same reference numerals. 12 and 13 show a part of the pair of rotor blades 51 for convenience of explanation.

The rotor blade 70 according to the third modification of the first embodiment has a damper member 71 in place of the damper member 42 constituting the rotor blade 40 (see FIG. 6) of the first embodiment. Is configured in the same manner as the rotor blade 40.

The damper member 71 includes a damper member main body 72, a plurality of contact portions 73, 75, and a pair of first and second inclined portions 77, 78 composed of the damper member main body 72 and the plurality of contact portions 73, 75. , Have.

The damper member main body 72 is a plate-shaped member having a mountain shape along the facing surfaces 52b of the pair of moving blades 51. The damper member main body 72 has a surface 72a facing the facing surface 52b of the pair of rotor blades 51, and a surface 72b arranged on the opposite side of the surface 72a.
The damper member main body 72 has a central portion that constitutes a part of a pair of first inclined portions 77, and an outside that is arranged outside the central portion and constitutes a part of a pair of second inclined portions 78. Has.

The surface 72a constituting the central portion of the damper member main body 72 is inclined at an inclination angle α with respect to the second virtual plane Vp2.
The surface 72a constituting the outside of the damper member main body 72 is inclined at an inclination angle β larger than the inclination angle α with respect to the second virtual plane Vp2.
That is, the damper member main body 72 has the same shape as the damper member 42 (see FIG. 4) of the first embodiment described above.

The plurality of contact portions 73 are provided on the surface 72a constituting the central portion of the damper member main body 72. The plurality of contact portions 73 project from the surface 72a toward the facing surface 52b.
The plurality of contact portions 73 are arranged in the axial direction Da in a state of being spaced apart from each other. The plurality of contact portions 73 are integrally formed with the damper member main body 72.

The plurality of contact portions 73 have contact surfaces 73a that come into contact with the facing surfaces 52b of the pair of rotor blades 51 when the rotor disk 47 (see FIG. 2) rotates at a medium speed. The contact surface 73a is inclined at an inclination angle α with respect to the second virtual plane Vp2.

The plurality of contact portions 75 are provided on the surface 72a constituting the outside of the damper member main body 72. The plurality of contact portions 75 are arranged in the axial direction Da at intervals. The plurality of contact portions 75 are integrally formed with the damper member main body 72.
The plurality of contact portions 75 have contact surfaces 75a that come into contact with the facing surfaces 52b of the pair of rotor blades 51 when the rotor disk 47 (see FIG. 2) rotates at a low speed. The contact surface 75a is inclined with respect to the second virtual plane Vp2 at an inclination angle β larger than the inclination angle α.

The pair of first inclined portions 77 constitutes the central portion of the damper member 71. The pair of first inclined portions 77 is configured to include a damper member main body 72 arranged in the central portion of the damper member 71, and a plurality of contact portions 73.

The pair of second inclined portions 78 are arranged outside the pair of first inclined portions 77. The pair of second inclined portions 78 constitutes the outside of the damper member 71.
The pair of second inclined portions 78 has a structure including a damper member main body 72 constituting the outside of the damper member 71 and a plurality of contact portions 75.

According to the rotor blade 70 according to the third modification of the first embodiment, a pair of first inclined portions 77 including a plurality of contact portions 73 arranged at intervals in the axial direction Da, and an axial Da in the axial direction Da. A pair of second inclined portions 78 arranged outside the pair of first inclined portions 77, including a plurality of contact portions 75 arranged at intervals, and by having the first inclined portion 77. It is possible to make the contact area of the pair of rotor blades 51 with the facing surface 52b different from the contact area of the second inclined portion 78 with the facing surface 52b of the pair of rotor blades 51.
Thereby, the frictional resistance generated when the facing surfaces 52b of the pair of rotor blades 51 and the damper member 71 come into contact with each other can be adjusted according to the rotation speed.

The blade 70 may be provided with the support member 61 (see FIG. 9) or the support member 66 (see FIG. 10) described above.

(Second embodiment)
The rotor blade 80 according to the second embodiment of the present invention will be described with reference to FIGS. 14 to 16. In FIGS. 14 and 15, the same components as those of the structure shown in FIG. 6 are designated by the same reference numerals. In FIGS. 14 to 16, the same components are designated by the same reference numerals.

The rotor blade 80 is configured in the same manner as the rotor blade 40 except that it has a damper member 81 in place of the damper member 42 constituting the rotor blade 40 of the first embodiment.

The damper member 81 has a mountain-shaped portion 82 and bent portions 83 and 84.
The mountain-shaped portion 82 has a mountain-shaped shape along the facing surface 52b of the pair of moving blades 51. The mountain-shaped portion 82 constitutes the central portion of the damper member 81. The central portion of the mountain-shaped portion 82 faces the gap H. The outside of the mountain-shaped portion 82 faces the facing surface 52b.
The mountain-shaped portion 82 has a contact surface 82a that comes into contact with the facing surfaces 52b of the pair of rotor blades 51 when the rotation speed of the rotor disk 47 (see FIG. 2) is high (an example of the first rotation speed).

The bent portions 83 and 84 are provided at both ends of the chevron portion 82 located in the circumferential direction of the rotor disk 47 so as to sandwich the chevron portion 82 from both sides. The bent portion 83 has an end surface 83a that comes into contact with the facing surface 52b of one of the rotor blades 51 due to the rotation of the rotor disk 47.
The bent portion 84 has an end surface 84a that comes into contact with the facing surface 52b of the other rotor blade 51 due to the rotation of the rotor disk 47.
The end faces 83a and 84a are arranged so as to project toward the facing surface 52b from the contact surface 82a of the mountain-shaped portion 82.

As a result, the end faces 83a and 84a come into contact with the facing surface 52b at the stage where the rotation speed of the rotor disk 47 is low (an example of the second rotation speed) (see FIG. 14). Then, the state of contact with the facing surface 52b is maintained even while the rotation speed of the rotor disk 47 changes from low speed to high speed (see FIG. 15).
The area of the end faces 83a and 84a is considerably smaller than the area of the contact surface 82a described above. Therefore, the frictional resistance generated when the end faces 83a and 84a are in contact with the facing surface 52b is much smaller than the frictional resistance generated when the contact surface 82a and the facing surface 52b are in contact with each other.

The bent portions 83 and 84 having the above configuration are contact suppressing members for suppressing the contact surface 82a of the chevron portion 82 from coming into contact with the facing surface 52b during low-speed rotation, which is an example of the second rotation speed. Functions as.
Therefore, the contact surface 82a of the mountain-shaped portion 82 is a facing surface of the pair of moving blades 51 when the rotor disk 47 rotates at high speed (an example of the first rotation speed) (when the centrifugal force becomes large). It comes into contact with the 52b and generates a large frictional resistance with the facing surface 52b (see FIG. 15).

That is, the damper member 81 increases the contact area of the pair of rotor blades 51 with the facing surfaces 52b when the rotation speed of the rotor disk 47 (see FIG. 2) is high, and as the rotation speed of the rotor disk 47 decreases. , The contact area of the pair of rotor blades 51 with the facing surface 52b is reduced.

As described above, by having the damper member 81 that increases the contact area of the pair of rotor blades 51 with the facing surface 52b when the rotation speed of the rotor disk 47 is high, resonance occurs when the rotation speed of the rotor disk 47 is high. When the above occurs, the vibration generated in the rotor blade 51 can be appropriately suppressed.

Further, as the rotation speed of the rotor disk 47 decreases (as the rotation speed of the rotor disk 47 deviates from the rotation speed at which resonance occurs), the contact area of the pair of rotor blades 51 with the facing surface 52b is reduced, thereby reducing the rated rotation speed. In, it is possible to reduce the frictional resistance generated between the facing surfaces 52b of the pair of rotor blades 51 and the damper member 81. This makes it possible to reduce variations in frequency and attenuation.

According to the rotor blade 80 of the second embodiment, when the rotor blade 47 has a high rotation speed, the mountain-shaped portion 82 that comes into contact with the facing surfaces 52b of the pair of rotor blades 51 and the rotation speed of the rotor disk 47 are low. By having the bent portions 83, 84 including the end faces 83a, 84a that come into contact with the facing surfaces 52b of the pair of rotor blades 51 in the step, the pair when resonance occurs when the rotation speed of the rotor disk 47 is high. It is possible to increase the contact area between the facing surface 52b of the moving blade 51 and the damper member 81.
As a result, when the rotation speed of the rotor disk 47 is high, it is possible to generate a large frictional resistance between the facing surface 52b of the pair of rotor blades 51 and the mountain-shaped portion 82, which is generated in the rotor blades. Vibration can be suppressed appropriately.
Further, it is possible to reduce the area between the facing surface 52b of the pair of rotor blades 51 and the damper member 81 during the rated rotation to reduce the variation in frequency and damping during the rated operation.

In the rotor blade 80 of the second embodiment, of the bent portions 83 and 84 provided in the mountain-shaped portion 82, the end surface 83a and the facing surface 52b of one of the bent portions 83 may be fixed.
By fixing the end surface 83a of the bent portion 83 and the facing surface 52b in this way, it is possible to maintain the posture of the damper member 81 with respect to the facing surface 52b of the pair of rotor blades 51. As a result, the facing surfaces 52b of the pair of rotor blades 51 and the damper member 81 can be brought into contact with each other in an appropriate state.

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 40,60,65,70,80 ... Moving wing body 41 ... Turbine cabin 42,71 , 81 ... Damper members 42a, 72a, 72b ... Surface 47A ... Fitting groove 50 ... Combustion gas flow path 52 ... Platform 52a ... Gap forming surface 52b ... Opposing surface 53 ... Blade root 54 ... Blade 55 ... Fuel line 56,77 ... First inclined portion 56a, 57a, 73a, 75a, 82a ... Contact surface 57, 78 ... Second inclined portion 59 ... Fuel control valve 61, 66 ... Support member 61a, 66a ... Support surface 61A, 66A ... One end 61B , 66B ... other end 72 ... damper member body 73,75 ... contact part 82 ... mountain-shaped part 83,84 ... bent part 83a, 84a ... end face A ... outside air Acom ... compressed air Ar ... axis C ... region Da ... axis direction Dau ... Axial upstream side Dad ... Axial downstream side Dc ... Circumferential Dr ... Radial Dr ... Radial outside Dri ... Radial inside F ... Fuel G ... Combustion gas H ... Gap O ... Target axis T ... Apex Vp1 ... First Virtual plane Vp2 ... Second virtual plane W1, W2 ... Width α, β ... Tilt angle

Claims (7)

A rotor disk that can rotate integrally with the spindle,
A plurality of blades mounted on the rotor disk and extending radially from the outer peripheral portion of the rotor disk,
A damper member that comes into contact with the facing surfaces of a pair of rotor blade platforms arranged adjacent to each other in the circumferential direction of the rotor disk.
Equipped with
The damper member closes the gap formed between the platforms of the pair of rotor blades when the rotor disk rotates, and with the facing surface of the platform of the pair of rotor blades according to the rotation speed of the rotor disk. By changing the contact area of
The damper member increases the contact area of the pair of rotor blades with the facing surface of the platform when the rotation speed of the rotor disk is the first rotation speed, and the rotation speed of the rotor disk is the first rotation speed. At a second rotation speed different from the rotation speed of, the contact area of the pair of rotor blades with the facing surface of the platform is reduced.
The facing surfaces of the pair of rotor blades are inclined surfaces that expand the diameter of the space formed between the platforms of the pair of rotor blades as they move from the blade portions of the rotor blades toward the rotor disk.
The damper member is a plate-shaped damper having a mountain shape along the facing surface of the pair of rotor blades, and has a plurality of inclined portions whose width increases outward from the center position of the damper member. death,
A rotor blade whose inclination angle of the plurality of inclined portions increases from the center position of the damper member toward the outside . The plurality of inclined portions each have a plurality of contact portions arranged in a direction in which the main shaft extends.
The moving blade body according to claim 1 , wherein the plurality of contact portions have contact surfaces that come into contact with facing surfaces of the pair of moving blades. The motion according to claim 1 or 2 , wherein the damper member is fixed to the contact portion of the platform which is in contact with the damper member when the rotation speed of the rotor disk is high among the platforms of the pair of rotor blades. Wing body. A rotor disk that can rotate integrally with the spindle,
A plurality of blades mounted on the rotor disk and extending radially from the outer peripheral portion of the rotor disk,
A damper member that comes into contact with the facing surfaces of a pair of rotor blade platforms arranged adjacent to each other in the circumferential direction of the rotor disk.
Equipped with
The damper member closes the gap formed between the platforms of the pair of rotor blades when the rotor disk rotates, and with the facing surface of the platform of the pair of rotor blades according to the rotation speed of the rotor disk. By changing the contact area of
The facing surface of the pair of rotor blades is an inclined surface that expands the diameter of the space formed on the platform of the pair of rotor blades from the blade portion of the pair of rotor blades toward the rotor disk.
The damper member has a mountain-shaped shape along the facing surfaces of the pair of rotor blades, and has a mountain-shaped portion that comes into contact with the facing surfaces of the pair of rotor blades when the rotation speed of the rotor disk is high.
Bent portions provided at both ends of the mountain-shaped portion in the circumferential direction and including end faces that come into contact with the facing surfaces of the pair of rotor blades at a stage where the rotation speed of the rotor disk is low.
A blade body with. The rotor blade body according to claim 4 , wherein the end surface of one of the bent portions and the platform of the bent portions provided at both ends of the mountain-shaped portion are fixed. The moving blade according to any one of claims 1 to 5 , wherein one end of the facing surface of the pair of moving blades is fixed to one of the facing surfaces and the support member has a support member that maintains the posture of the damper member. body. A rotary machine having a rotor blade according to any one of claims 1 to 6 .

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