JP5675282B2 - Rotor body and rotating machine - Google Patents

Description

The present invention rotating blade body constituting the rotary machine is mounted a gas turbine, steam turbine, etc. in a jet engine, to the rotary machine.

  A general gas turbine includes a compressor, a combustor, and a turbine. The air taken in from the air intake port is compressed by the compressor to become high-temperature and high-pressure compressed air. In the combustor, the fuel is supplied to the compressed air and burned, so that the high-temperature and high-pressure is burned. The combustion gas (working fluid) is obtained, the turbine is driven by the combustion gas, and the generator connected to the turbine is driven.

  A rotor blade body used in such a compressor or turbine of a gas turbine includes a rotor disk that rotates integrally with a main shaft, and a plurality of rotor blades that are assembled so as to extend radially from the outer periphery of the rotor disk. Composed. In this case, the plurality of rotor blades are arranged such that each blade root portion engages with a groove formed in the outer peripheral portion of the rotor disk, and a seal pin is in contact between adjacent platforms. The seal pin extends along the direction of the rotation axis, and performs a sealing function for preventing leakage of combustion gas and a damping function for attenuating vibration of the moving blades.

  Examples of such a conventional moving blade body are described in Patent Documents 1 and 2 below. The blade damper described in Patent Document 1 is received in a gap formed between adjacent platforms of the blade, and the vibration of the blade is attenuated by frictional engagement with the platform, and the air has a corresponding gap. It prevents it from passing. Further, the moving blade body described in Patent Document 2 is provided with a seal pin extending along the rotation axis direction in the gap between the platform portions of the moving blades adjacent to each other in the circumferential direction, and passes through the seal pin coaxially. A through hole is provided.

JP 2002-030902 A JP 2006-214367 A

  In the conventional moving blade body described above, a blade damper or a seal pin is interposed between adjacent moving blades to prevent leakage of combustion gas and to attenuate vibration of the moving blade. In this case, when the moving blade body rotates, centrifugal force acts on the blade damper (seal pin), and a reaction force is received from the contacting moving blade, and a frictional force is generated on the contact surface between the moving blade and the blade damper. The exciting force of the moving blade can be attenuated by this frictional force.

  However, the moving blade body is different in the exciting force of the moving blade generated by the shape of the rotor disk and the moving blade, the steady rotation speed, etc., and a blade damper or a seal pin is simply interposed between the adjacent moving blades. It is difficult to properly attenuate the excitation force generated in the rotor blades.

The present invention solves the above-described problems, and an object thereof is to provide a moving blade body and a rotating machine that can appropriately suppress vibration generated in the moving blade.

  In order to achieve the above object, a rotor blade of the present invention includes a rotor disk that can rotate integrally with a main shaft, and a plurality of rotor blades that are mounted so as to extend radially from the outer periphery of the rotor disk; A damper member mounted in a gap between platforms of the moving blades adjacent in the circumferential direction, and an adjustment member interposed between the platform and the damper member to adjust a contact angle with the damper member. It is characterized by comprising.

  Therefore, an adjustment member capable of adjusting a contact angle with respect to the damper member is interposed between the platform and the damper member. When the contact angle is adjusted, the damper is moved from the platform via the adjustment member when the moving blade body rotates. The reaction force input to the member will increase or decrease. Therefore, an optimal contact angle can be selected according to the shape of the moving blade body, the number of rotations, and the like, and vibration generated in the moving blade can be appropriately suppressed.

  In the moving blade body of the present invention, an inclined surface is provided on at least one of the facing surfaces of the platforms adjacent in the circumferential direction so that the center side of the main shaft is enlarged with respect to the radial direction of the rotor disk. And an attachment recess capable of positioning the adjusting member is provided on the inclined surface.

  Therefore, by mounting the adjustment member in the mounting recess, the adjustment member can be easily and stably positioned, and vibration generated in the moving blade can be appropriately suppressed.

  In the moving blade body of the present invention, the adjustment member is made of a softer material than the platform and the damper member.

  Therefore, the soft adjustment member will wear due to long-term use, making it unnecessary to change the moving blade and damper member, which are difficult to change, and maintaining a stable damping function over the long term simply by replacing the worn adjustment member Can do.

According to the moving blade body and the rotating machine of the present invention, since the adjusting member capable of adjusting the contact angle with the damper member is interposed between the platform and the damper member, vibration generated in the moving blade is appropriately suppressed. be able to.

FIG. 1 is a schematic configuration diagram showing a gas turbine equipped with a moving blade body according to an embodiment of the present invention. FIG. 2 is a schematic diagram illustrating a moving blade in a gas turbine. FIG. 3 is a waist cross-sectional view of the moving blade body showing the attached state of the moving blade. FIG. 4 is a cross-sectional view of the main part of the rotor blade body to which the damper pin is attached. FIG. 5 is a cross-sectional view of the main part of the rotor blade body on which the damper pin and the adjustment piece are mounted. FIG. 6 is a cross-sectional view of the main part of the rotor blade body on which the damper pin and the adjustment piece are mounted. FIG. 7 is a graph showing the reaction force / centrifugal force with respect to the angle of the adjustment piece.

  Exemplary embodiments of a rotor blade according to the present invention will be described below in detail with reference to the accompanying drawings. In addition, this invention is not limited by this Example, Moreover, when there exists multiple Example, what comprises combining each Example is also included.

  FIG. 1 is a schematic configuration diagram showing a gas turbine equipped with a moving blade body according to an embodiment of the present invention, FIG. 2 is a schematic diagram showing moving blades in the gas turbine, and FIG. 3 is an attached state of the moving blades. 4 is a cross-sectional view of the main part of the moving blade body on which the damper pin is mounted, and FIGS. 5 and 6 are cross-sectional views of the main part of the moving blade body on which the damper pin and the adjustment piece are mounted. FIG. 7 is a graph showing the reaction force / centrifugal force with respect to the angle of the adjustment piece.

  As shown in FIG. 1, the gas turbine includes a compressor 11, a combustor 12, and a turbine 13. A generator (not shown) is connected to the gas turbine and can generate power.

  The compressor 11 has an air intake 20 for taking in air, an inlet guide vane (IGV) 22 is disposed in the compressor casing 21, and a plurality of stationary vanes 23 and moving blades 24 are arranged in the front-rear direction (described later). Are arranged alternately in the axial direction of the rotor 32, and the bleed chambers 25 are provided outside thereof. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it. In the turbine 13, a plurality of stationary blades 27 and moving blades 28 are alternately disposed in a turbine casing 26 in the front-rear direction (the axial direction of a rotor 32 described later). An exhaust chamber 30 is disposed downstream of the turbine casing 26 via an exhaust casing 29, and the exhaust chamber 30 has an exhaust diffuser 31 that is continuous with the turbine 13.

  A rotor (main shaft) 32 is positioned so as to penetrate through the compressor 11, the combustor 12, the turbine 13, and the central portion of the exhaust chamber 30. The end of the rotor 32 on the compressor 11 side is rotatably supported by the bearing portion 33, while the end of the exhaust chamber 30 side is rotatably supported by the bearing portion 34. In the rotor 32, a plurality of rotor disks 35 to which the rotor blades 24 are mounted are stacked and fixed in the compressor 11, and a plurality of rotor disks 36 to which the rotor blades 28 are mounted in the turbine 13. The driving shaft of the generator (not shown) is connected to the end on the exhaust chamber 30 side.

  In this gas turbine, the compressor casing 21 of the compressor 11 is supported by the legs 37, the turbine casing 26 of the turbine 13 is supported by the legs 38, and the exhaust chamber 30 is supported by the legs 39. .

  Therefore, the air taken in from the air intake port 20 of the compressor 11 passes through the inlet guide vane 22, the plurality of stationary vanes 23, and the moving blades 24 and is compressed to become high-temperature and high-pressure compressed air. A predetermined fuel is supplied to the compressed air in the combustor 12 and burned. Then, the high-temperature and high-pressure combustion gas (working fluid) that is the working fluid generated by the combustor 12 passes through the plurality of stationary blades 27 and the moving blades 28 that constitute the turbine 13 to drive and rotate the rotor 32. Then, the generator connected to the rotor 32 is driven. On the other hand, the energy of the exhaust gas (combustion gas) is converted into pressure by the exhaust diffuser 31 in the exhaust chamber 30 and decelerated before being released to the atmosphere.

  In the gas turbine configured as described above, the rotor blade body of the present embodiment is applied to the turbine 13 and can rotate integrally with the rotor 32 as shown in FIGS. 2 and 3. It has a disk 36 and a plurality of blades 28 mounted so as to extend radially from the outer periphery of the rotor disk 36.

  The moving blade 28 includes a blade root portion 41, a platform 42, and a wing portion 43. The blade root portion 41 has a so-called Christmas tree shape in cross section when viewed from the axial direction of the rotor 32, and can be fixed by being fitted to the rotor disk 36 from the thickness direction. The platform 42 has a pedestal shape that connects the blade root portion 41 and the blade portion 43, and has a curved plate shape integrated with the blade root portion 41 so as to cover the outer periphery of the rotor disk 36. The wing portion 43 has a streamlined cross-sectional shape, and extends while being gradually twisted while ensuring this shape. The base end portion is fixed to the platform 42 and the tip end portion is inside a casing (not shown). It extends to the wall surface and functions to allow the combustion gas to flow smoothly.

  On the other hand, in the rotor disk 36, fitting grooves 51 having substantially the same shape as the cross-sectional shape of the blade root 41 of the rotor blade 28 are formed on the outer periphery along the axial direction at equal intervals in the circumferential direction. Each fitting groove 51 is fixed by inserting the blade root 41 of the rotor blade 28 from the axial direction. Then, by assembling the plurality of moving blades 28 to the rotor disk 36, a moving blade body in which the blade portions 43 of the plurality of moving blades 28 extend radially from the outer periphery of the rotor disk 36 is configured.

  The moving blade body of the present embodiment configured as described above includes a damper pin (damper member) 61 mounted in a gap between the platforms 42 of the moving blades 28 adjacent in the circumferential direction, and between the platform 42 and the damper pin 61. An adjustment piece (adjustment member) 62 that is interposed and can adjust the contact angle with respect to the damper pin 61 is provided. In this case, an inclined surface is provided on at least one of the opposing surfaces of the platforms 42 adjacent to each other in the circumferential direction so that the center side of the rotor 32 expands with respect to the radial direction of the rotor disk 36. A mounting recess is provided in which the adjustment piece 62 can be positioned.

That is, as shown in FIG. 4, among the platforms 42 of the adjacent moving blades 28, one platform 42a has a side surface 71a parallel to the radial direction of the rotor disk 36, and the other platform 42b is a rotor disk. It has the inclined surface 71b used as the side surface which the center side of the rotor 32 expands with respect to 36 radial directions. The platform 42 b has a mounting recess 72 formed on the inclined surface 71 b, and the mounting recess 72 is a groove along the axial direction of the rotor 32. In this embodiment, the inclined surface 71b (mounting recess 72), the diameter direction of the rotor 32, i.e., the angle is set to theta ₀ to radiant direction of the rotor disc 36.

  A damper pin 61 is interposed between the side surface 71a of the platform 42a and the inclined surface 71b (mounting recess 72) of the platform 42b. In this case, it is preferable that the damper pin 61 is disposed in the mounting recess 72 and the end is supported by a support member (not shown).

In the present embodiment, the contact angle of the platform 42b with respect to the damper pin 61 can be adjusted. That is, as shown in FIG. 5, the adjustment piece 62a is a plate member that has a thin upper end portion and a thick lower end portion and is long in the axial direction of the rotor disk 36, and is formed on the inclined surface 71b of the platform 42b. It fits into the formed mounting recess 72. Therefore, the damper pin 61 is interposed between the side surface 71a of the platform 42a and the adjustment piece 62a supported by the mounting recess 72 of the inclined surface 71b of the platform 42b. In this case, the angle of the adjustment piece 62a with respect to the radial direction of the rotor 32, that is, the radial direction of the rotor disk 36 is set to θ ₁ (θ ₁ <θ ₀ ).

Further, as shown in FIG. 6, the adjustment piece 62b is a plate member having a thick upper end and a thin lower end, and is long in the axial direction of the rotor disk 36, and is formed on the inclined surface 71b of the platform 42b. It fits into the formed mounting recess 72. Therefore, the damper pin 61 is interposed between the side surface 71a of the platform 42a and the adjustment piece 62b supported by the mounting recess 72 of the inclined surface 71b of the platform 42b. In this case, in the adjustment piece 62b, the angle with respect to the radial direction of the rotor 32, that is, the radial direction of the rotor disk 36 is set to θ ₂ (θ ₁ <θ ₀ <θ ₂ ).

  Here, each adjustment piece 62 (62a, 62b) is made of a softer material than the platform 42 (42a, 42b) and the damper pin 61.

  Therefore, as shown in FIG. 4, when the rotor disk 36 is rotated together with the rotor 32, and each rotor blade 28 is rotated, the centrifugal force CF acts on the damper pin 61. Therefore, the side surface 71a of one platform 42a is applied to the damper pin 61. The reaction force Na acts, and the reaction force Nb acts on the damper pin 61 from the inclined surface 71b of the other platform 42b. On the other hand, during operation of the gas turbine, an excitation force from the combustion gas acts on each rotor blade 28, so that each rotor blade 28 vibrates, and a frictional force is generated at the contact portion between the platforms 42a, 42b and the damper pin 61. Occur. As a result, the frictional force generated at the contact portion between the platforms 42 a and 42 b and the damper pin 61 attenuates the excitation force of the moving blade 28.

  However, gas turbines have different rated rotational speeds depending on the model, and have a specific frequency corresponding to the frequency (excitation force) at this time. For this reason, any type of gas turbine is not capable of attenuating the excitation force of the moving blade 28 by the damper pin 61.

  Therefore, as shown in FIGS. 5 and 6, the platform 42 b (adjustment pieces 62 a, 62 b) with respect to the damper pin 61 is mounted by attaching the adjustment pieces 62 a, 62 b having different shapes to the mounting recess 72 formed in the inclined surface 71 b of the platform 42 b. The contact angle of 62b) is changed. Therefore, the frictional force generated between the damper pin 61 and the platform 42b (adjustment pieces 62a and 62b) changes, and it becomes possible to adjust to the frictional force corresponding to the specific frequency of the specific gas turbine.

  That is, the centrifugal force acting on the damper pin 61 is CF, the reaction force acting on the damper pin 61 from the side surface 71a of one platform 42a is Na, and the other platform 42b (the inclined surface 71b, the adjustment pieces 62a and 62b) acts on the damper pin 61. Let Nb be the reaction force. In addition, an inclination angle of the platform 42b (inclined surface 71b, adjustment pieces 62a and 62b) with respect to the damper pin 61 is defined as θ. At this time, the reaction force Na, Nb / centrifugal force CF with respect to the inclination angle θ is represented in the graph shown in FIG. Here, N / CF is the sum of Na / CF and Nb / CF.

  As can be seen from this graph, when the inclination angle θ increases, the reaction force / centrifugal force N / CF decreases, and is generated between the platform 42b (the inclined surface 71b and the adjustment pieces 62a and 62b) and the damper pin 61. The frictional force is also reduced. That is, by using the appropriate adjustment pieces 62a and 62b, the frictional force with the damper pin 61 is adjusted to obtain the optimum frictional force for a specific gas turbine, and sufficient damping is applied to appropriately adjust the moving blade 28. Generation of vibration can be suppressed.

  In the case of the moving blade body mounted on the turbine 13 of the gas turbine as in the present embodiment, the blade portion 43 is exposed to a high temperature atmosphere by the high temperature combustion gas, so that the excessively generated moving blade 28 itself is excessive. It is necessary to suppress the temperature rise. Therefore, a gap for circulating cooling air is provided by the outer peripheral surface of the rotor disk 36 and the portion of the moving blade 28 adjacent in the circumferential direction that corresponds to the blade root 41 from the platform 42. As a result, when the cooling air flows through the gap, heat exchange is directly performed with the moving blades 28, and the moving blades 28 can be cooled to suppress an increase in temperature. However, if the combustion gas leaks excessively from the gaps between the platforms 42 in the adjacent moving blades 28, the turbine efficiency is lowered. Therefore, the above-described damper pin 61 functions as a seal pin that prevents excessive leakage of the combustion gas.

  Thus, in the moving blade body of the present embodiment, the rotor disk 36 that can rotate integrally with the rotor 32 and a plurality of moving blades that are mounted so as to extend radially from the outer periphery of the rotor disk 36. 28, a damper pin 61 mounted in a gap between the platforms 42 of the rotor blades 28 adjacent to each other in the circumferential direction, and an adjustment piece 62 that is interposed between the platform 42 and the damper pin 61 to adjust a contact angle with respect to the damper pin 61. And are provided.

  Accordingly, an adjustment piece 62 capable of adjusting the contact angle with respect to the damper pin 61 is interposed between the platform 42 and the damper pin 61. When the contact angle is adjusted, the adjustment piece 62 is removed from the platform 42 when the moving blade 28 rotates. The reaction force input to the damper pin 61 through the distance increases or decreases. For this reason, an optimal contact angle can be selected according to the shape and the rotational speed of the moving blade 28, and vibration generated in the moving blade 28 can be appropriately suppressed.

  Further, in the moving blade body of the present embodiment, at least one of the facing surfaces of the platforms 42 adjacent to each other in the circumferential direction is inclined so that the center side of the rotor 32 expands with respect to the radial direction of the rotor disk 36. A surface 71b is provided, and an attachment recess 72 capable of positioning the adjustment piece 62 is provided on the inclined surface 71b. Therefore, by mounting the adjustment piece 62 in the mounting recess 72, the adjustment piece 62 can be easily and stably positioned, and vibration generated in the moving blade 28 can be appropriately suppressed.

  Moreover, in the moving blade body of the present embodiment, the adjustment piece 62 is made of a soft material than the platform 42 and the damper pin 61. Accordingly, the soft adjustment piece 62 is worn by long-term use, making it unnecessary to change the moving blade 28 and the damper pin 61 that are difficult to change, and providing a long-term stable damping function simply by replacing the worn adjustment piece 62. Can be maintained.

  In the above-described embodiment, the adjustment piece 62 is interposed between the platform 42b and the damper pin 61. However, the adjustment piece may be interposed between the platform 42a and the damper pin 61, or both. May be.

  In the above-described embodiments, the moving blade body according to the present invention is applied to the turbine 13 of the gas turbine. However, the moving blade body may be applied to the compressor 11 and is not limited to the gas turbine. It can be applied to other rotating machines.

  The moving blade body according to the present invention can appropriately suppress vibration generated in the moving blade by interposing an adjusting member capable of adjusting a contact angle with respect to the damper member between the moving blade platform and the damper member. It can be applied to any rotating machine.

11 Compressor 12 Combustor 13 Turbine 28 Rotor blade 32 Rotor (main shaft)
36 Rotor disc 41 Blade root 42, 42a, 42b Platform 43 Wing 61 Damper pin (damper member)
62, 62a, 62b Adjustment piece (adjustment member)
71b Inclined surface 72 Mounting recess

Claims (4)

A rotor disk that can rotate integrally with the main shaft;
A plurality of moving blades mounted so as to extend radially from the outer periphery of the rotor disk;
A damper member installed in a gap between the blade platforms adjacent in the circumferential direction;
An adjustment member interposed between the platform and the damper member and capable of adjusting a contact angle with the damper member;
Equipped with a,
At least one of the opposing surfaces of the platforms adjacent to each other in the circumferential direction is provided with an inclined surface that enlarges the center side of the main shaft with respect to the radial direction of the rotor disk, and the adjustment is performed on the inclined surface. A mounting recess capable of positioning the member is provided,
A moving blade body characterized by that. The moving blade body according to claim 1 , wherein the adjustment member is made of a softer material than the platform and the damper member. A rotor disk that can rotate integrally with the main shaft;
A plurality of moving blades mounted so as to extend radially from the outer periphery of the rotor disk;
A damper member installed in a gap between the blade platforms adjacent in the circumferential direction;
An adjustment member interposed between the platform and the damper member and capable of adjusting a contact angle with the damper member;
Equipped with a,
The adjustment member is made of a soft material than the platform and the damper member,
A moving blade body characterized by that.   A rotating machine comprising the blade body according to any one of claims 1 to 3.

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