JP7614932B2 - Rotating Machinery - Google Patents

Description

This disclosure relates to rotating machines.

Patent Document 1 discloses a rotary machine having a rotor with multiple blades fixed in a line in the circumferential direction of the rotor shaft. In this rotary machine, the multiple blades are arranged in a circumferential direction such that blades with heavy tips and blades with light tips are alternately arranged. With this configuration, self-excited vibration, forced vibration, random vibration, etc. of the multiple blades can be suppressed while the rotary machine is in operation.

JP 2018-150857 A

However, the configuration described in Patent Document 1 is intended for rotor blades of a rotary machine.
Some rotary machines are provided with an inlet guide vane (IGV) to adjust the flow rate of the working fluid introduced from the outside. The inlet guide vane is arranged further upstream of the rotor blade row arranged at the most upstream side in the flow direction of the working fluid in the casing of the rotary machine. The inlet guide vane extends from the inner peripheral surface of the casing toward the inside in the radial direction of the casing. The inlet guide vane is configured to be rotatable around a shaft portion extending in the radial direction, and by changing the angle around the shaft portion, the flow rate of the working fluid introduced into the casing is adjusted according to the load conditions of the rotary machine, etc.
Even with this type of inlet guide vane, unstable vibrations such as flutter can occur in the inlet guide vane under high-load conditions where the flow velocity of the working fluid is high. For this reason, there is a demand for the development of technology that can effectively suppress the vibration of the inlet guide vane.

The present disclosure has been made to solve the above problems, and aims to provide a rotating machine that can effectively suppress vibration of the inlet guide vanes.

In order to solve the above problems, the rotary machine according to the present disclosure includes a rotor, a casing, and an inlet guide vane section. The rotor includes a rotor shaft and a row of moving blades. The rotor shaft rotates around an axis. The row of moving blades is fixed to the rotor shaft. The casing covers the rotor. The inlet guide vane section is disposed inside the casing on a first side in an axial direction in which the axis extends relative to the row of moving blades. The inlet guide vane section includes a plurality of movable vanes, a drive ring, and a plurality of link mechanisms. The plurality of movable vanes are disposed at intervals in a circumferential direction around the axis. The plurality of movable vanes are rotatable around a shaft portion extending in a radial direction centered on the axis. The drive ring is provided radially outside the plurality of movable vanes and is continuous in the circumferential direction. The drive ring is driven to be displaced in the circumferential direction. One link end of each of the plurality of link mechanisms is connected to the shaft portion of each of the plurality of movable vanes. The other link end of the plurality of link mechanisms is connected to the drive ring. The plurality of link mechanisms rotate each of the plurality of movable blades around the shaft portion when the drive ring is displaced in the circumferential direction. Each of the plurality of link mechanisms includes a plurality of link pieces arranged between the one link end and the other link end, and a pin that rotatably connects the plurality of link pieces to each other, and at least two of the plurality of link mechanisms include a dynamic vibration absorber, so that their natural frequencies are different from each other.
A rotary machine according to the present disclosure includes a rotor including a rotor shaft rotating about an axis and a row of rotor blades fixed to the rotor shaft, a casing covering the rotor, and an inlet guide vane portion disposed inside the casing on a first side in an axial direction in which the axis extends relative to the row of rotor blades, the inlet guide vane portion including a plurality of movable vanes disposed at intervals in a circumferential direction about the axis and rotatable about a shaft portion extending in a radial direction centered on the axis, and a rotor blade provided radially outward of the plurality of movable vanes and continuing in the circumferential direction, the rotor blades being arranged on the first side of the casing in an axial direction in which the axis extends. and a plurality of link mechanisms, each having one link end connected to the shaft portion of each of the plurality of movable blades and the other link end connected to the drive ring, such that when the drive ring is displaced in the circumferential direction, each of the plurality of link mechanisms is provided with a damping mechanism that damps vibrations generated in the link mechanism, and at least two of the plurality of link mechanisms have damping characteristics in the damping mechanism that are different from each other.

The rotating machine disclosed herein can effectively suppress vibration of the inlet guide vane.

1 is a diagram illustrating a schematic configuration of a gas turbine including a compressor as a rotary machine according to an embodiment of the present disclosure. 1 is a cross-sectional view showing a schematic configuration of a compressor as a rotary machine according to a first embodiment of the present disclosure. FIG. 2 is a view showing an inlet guide vane portion provided in the compressor according to the first embodiment of the present disclosure, as viewed from the axial direction. FIG. 2 is a perspective view showing a portion of a movable vane, a link mechanism, and a drive ring of the inlet guide vane portion according to the first embodiment of the present disclosure. FIG. 2 is an enlarged view showing a portion of the inlet guide vane portion according to the first embodiment of the present disclosure. FIG. 11 is a diagram showing a configuration of an inlet guide vane portion according to a second embodiment of the present disclosure. FIG. 13 is a diagram illustrating a configuration of an inlet guide vane portion according to a modified example of an embodiment of the present disclosure. FIG. 13 is a diagram showing a configuration of an inlet guide vane portion according to another modified example of the embodiment of the present disclosure.

First Embodiment
(Gas Turbine System Configuration)
Hereinafter, a rotating machine according to an embodiment of the present disclosure will be described with reference to FIGS. 1 to 5. FIG.

As shown in FIG. 1 , the rotary machine in this embodiment is, for example, a compressor 10 provided in a gas turbine 1 .
The gas turbine 1 includes a compressor 10 as the rotary machine, a combustor 2, a turbine 3, and a rotor 11. The compressor 10 compresses air taken in from the outside to generate high-pressure air. The combustor 2 burns a mixture of the high-pressure air compressed by the compressor 10 and fuel to generate high-temperature, high-pressure combustion gas. The turbine 3 is driven by the combustion gas generated by the combustor 2. The rotational driving force of the turbine 3 is transmitted to the compressor 10 via the rotor 11. In this way, the compressor 10 is driven.

(Compressor configuration)
As shown in Fig. 2, the compressor 10 includes at least a rotor 11 rotating about an axis Ar, a casing 15, a plurality of stator vane rows 17, and an inlet guide vane section 20A. In the following description, the direction in which the axis Ar extends is referred to as the axial direction Da, the circumferential direction centered on the axis Ar is simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar is referred to as the radial direction Dr. One side of the axial direction Da is referred to as the first side Da1, and the opposite side is referred to as the second side Da2. The side approaching the axis Ar in the radial direction Dr is referred to as the inner side Dri of the radial direction Dr, and the opposite side is referred to as the outer side Dro of the radial direction Dr.

The rotor 11 includes a rotor shaft 12 and multiple rotor blade rows 13. The rotor shaft 12 extends in the axial direction Da, centered on the axis Ar. The multiple rotor blade rows 13 are attached to the rotor shaft 12. The multiple rotor blade rows 13 are aligned in the axial direction Da. Each rotor blade row 13 includes multiple rotor blades aligned in the circumferential direction Dc.

The casing 15 is cylindrical and extends in the axial direction Da with the axis Ar at its center. The casing 15 covers the rotor 11 from the outside Dro in the radial direction Dr.

The multiple stator vane rows 17 are provided on the inner side Dri of the casing 15 in the radial direction Dr. The multiple stator vane rows 17 are arranged at intervals in the axial direction Da. Each stator vane row 17 is arranged on the second side Da2 in the axial direction Da with respect to each of the multiple rotor blade rows 13. The rotor blade rows 13 and the stator vane rows 17 are arranged alternately in the axial direction Da. Each stator vane row 17 has multiple stator vanes arranged in the circumferential direction Dc.

(Configuration of inlet guide wing section)
The inlet guide vane section 20A is disposed inside the casing 15. The inlet guide vane section 20A adjusts the flow rate of air taken into the casing 15 from an inlet port formed in the casing 15. The inlet guide vane section 20A is disposed on a first side Da1 in the axial direction Da with respect to the multiple rotor blade rows 13. The inlet guide vane section 20A is disposed on the first side Da1 in the axial direction Da with respect to the first stage rotor blade row 13A located on the furthest first side Da1 in the axial direction Da.

As shown in FIG. 3, the inlet guide vane section 20A includes a frame 21, a plurality of movable vanes 22, a drive ring 25, and a plurality of link mechanisms 30.
The frame 21 has an annular shape and forms a part of the axial direction Da of the casing 15. As shown in Fig. 4, the frame 21 has a plurality of blade retaining holes 21h. The plurality of blade retaining holes 21h are formed at intervals in the circumferential direction Dc. Each of the blade retaining holes 21h penetrates the frame 21 in the radial direction Dr.

A center hub 26 is provided on the inner side Dri in the radial direction Dr of the frame 21. The center hub 26 has a cylindrical shape extending in the axial direction Da. A plurality of blade retaining recesses 26a are formed on the outer peripheral surface of the center hub 26. The plurality of blade retaining recesses 26a are formed at intervals in the circumferential direction Dc. Each blade retaining recess 26a is recessed from the outer peripheral surface of the center hub 26 to the inner side Dri in the radial direction Dr.

The multiple movable blades 22 are provided on the inner side Dri of the frame 21 in the radial direction Dr. The multiple movable blades 22 are provided at intervals in the circumferential direction Dc. Each movable blade 22 integrally comprises a blade body 23 and a shaft portion 24.

The blade body 23 is a so-called inlet guide vane (IGV). The blade body 23 is arranged in such a manner that its blade length direction coincides with the radial direction Dr. One end 23a in the blade length direction, located on the inside Dri of the radial direction Dr of the blade body 23, is inserted into a blade holding recess 26a formed in the center hub 26 and is supported so as to be freely rotatable around the central axis Cs of the shaft portion 24.

The shaft portion 24 is integrally provided on the blade body 23 at the other end 23b in the blade length direction located on the outer side Dro in the radial direction Dr. The shaft portion 24 is generally cylindrical and extends from the other end 23b of the blade body 23 along the central axis Cs to the outer side Dro in the radial direction Dr. The shaft portion 24 is inserted into a blade retaining hole 21h formed in the frame 21 and is supported so as to be rotatable around the central axis Cs. The tip 24s of the shaft portion 24 on the outer side Dro in the radial direction Dr protrudes toward the outer side Dro in the radial direction Dr of the frame 21.

The drive ring 25 is provided on the outer side Dro of the casing 15 in the radial direction Dr. The drive ring 25 is annular and continuous in the circumferential direction Dc around the axis Ar, and is supported by the casing 15 so as to be displaceable in the circumferential direction Dc. The drive ring 25 may be divided into multiple parts in the circumferential direction Dc. The drive ring 25 is driven by an actuator (not shown) so as to be displaced along the circumferential direction Dc.

A link mechanism 30 is provided for each of the multiple movable wings 22. These multiple link mechanisms 30 rotate each of the multiple movable wings 22 around the central axis Cs of the shaft portion 24. Each link mechanism 30 has multiple link pieces 31 and multiple pins 32. In this embodiment, each link mechanism 30 has a first link piece 33 and a second link piece 34 as the multiple link pieces 31. In this embodiment, each link mechanism 30 has a first pin 35 and a second pin 36 as the multiple pins 32.

One end 33a of the first link piece 33 is fixed to the shaft portion 24 so as not to be rotatable around the central axis Cs. The other end 33b of the first link piece 33 is rotatably connected to one end 34a of the second link piece 34 via the first pin 35. As a result, the first link piece 33 and the second link piece 34 are connected so as to be rotatable around the first pin 35.

The other end 34b of the second link piece 34 is connected to the drive ring 25 via the second pin 36. The second link piece 34 is supported by the drive ring 25 so as to be freely rotatable around the second pin 36.

In this way, one end 33a of the first link piece 33 forming one link end 30a of each link mechanism 30 is connected to the shaft portion 24 of each movable wing 22. The other end 34b of the second link piece 34 forming the other link end 30b of each link mechanism 30 is connected to the drive ring 25.

In such an inlet guide vane section 20A, the drive ring 25 is displaced in the circumferential direction Dc by being rotated around the axis Ar (see FIG. 3) by an actuator (not shown). When the drive ring 25 is displaced in the circumferential direction Dc, the displacement is transmitted to the shaft portion 24 via the second link piece 34 and the first link piece 33. When the first link piece 33 swings around the shaft portion 24, the vane body 23 of the movable vane 22 rotates around the central axis Cs together with the shaft portion 24. As a result, the angle (opening) of the vane body 23 changes during the flow of fluid on the inner side Dri of the radial direction Dr of the casing 15, and the flow rate of the fluid taken into the casing 15 is adjusted.

5, in the inlet guide wing portion 20A, at least two of the multiple link mechanisms 30 have different structures. At least two of the multiple link mechanisms 30 have at least one of the weight, rigidity, and dimensions of the link piece 31 and the pin 32 that are different from each other. In this embodiment, at least two of the multiple link mechanisms 30 have different diameters of the pins 32 (first pin 35, second pin 36). In this embodiment, as the multiple link mechanisms 30, a link mechanism 30A having a large diameter pin 32A and a link mechanism 30B having a small diameter pin 32B are alternately arranged in the circumferential direction Dc. The diameter of the large diameter pin 32A is larger than the diameter of the small diameter pin 32B. The diameter of the large diameter pin 32A can be set to be, for example, 1.05 times or more, more preferably 1.10 times, the diameter of the small diameter pin 32B. As a result, the large diameter pin 32A and the small diameter pin 32B have different rigidity and weight. The link mechanism 30A with the large diameter pin 32A has higher rigidity than the link mechanism 30B with the small diameter pin 32B.

(Action and Effect)
The compressor 10 of the above embodiment includes a plurality of link mechanisms 30 that connect each of the plurality of movable vanes 22 constituting the inlet guide vane section 20A to the drive ring 25. At least two of the plurality of link mechanisms 30 have different structures. The link mechanisms 30 with different structures have different vibration characteristics. Therefore, the inlet guide vane section 20A has an imbalance in vibration characteristics between the plurality of movable vanes 22 and the link mechanisms 30 arranged in the circumferential direction Dc. This makes it possible to suppress the occurrence of unstable vibrations such as flutters in the inlet guide vane section 20A even under high load conditions where the flow velocity of the working fluid is high. As a result, it becomes possible to effectively suppress the vibration of the inlet guide vane.

In the above embodiment, in the multiple link mechanisms 30 each having multiple link pieces 31 and pins 32, the vibration characteristics of at least two of the multiple link mechanisms 30 can be made different by varying the link pieces 31 and pins 32.

In the above embodiment, the vibration characteristics of at least two link mechanisms 30 can be made different by making at least one of the weight, rigidity, and dimensions of at least one of the link pieces 31 and the pins 32 different.

(Modification of the embodiment)
In the above embodiment, the link mechanism 30A having the large diameter pin 32A and the link mechanism 30B having the small diameter pin 32B are arranged alternately in the circumferential direction Dc, but this is not limited to the above.
For example, a plurality of groups of link mechanisms 30B in which a plurality of link mechanisms 30B having small diameter pins 32B are arranged in the circumferential direction Dc may be provided, and these groups and link mechanisms 30A having large diameter pins 32A may be arranged alternately. In other words, one link mechanism 30A may be arranged for a plurality of link mechanisms 30B in the circumferential direction Dc. Similarly, for example, a plurality of groups of link mechanisms 30A in which a plurality of link mechanisms 30A having large diameter pins 32A are arranged in the circumferential direction Dc may be provided, and these groups and link mechanisms 30B having small diameter pins 32B may be arranged alternately. Furthermore, the groups of link mechanisms 30A and the groups of link mechanisms 30B may be arranged alternately.
Furthermore, the link mechanism 30A having the large diameter pin 32A and the link mechanism 30B having the small diameter pin 32B may be arranged randomly without any regularity in the circumferential direction Dc.
Furthermore, the multiple link mechanisms 30 may be provided with pins 32 having three or more different diameters.

In addition, in the above embodiment, the diameter dimension of the pin 32 is made different in order to make the structure of the multiple link mechanisms 30 different, but this is not limited to this. For example, at least two of the multiple link mechanisms 30 may have different structures by making the thickness of the link piece 31 different in the multiple link mechanisms 30.

Furthermore, the diameter of the pin 32 and the thickness of the link piece 31 may be different among the multiple link mechanisms 30 .
In addition, the weight, rigidity, material, etc. of the pins 32 and the link pieces 31 may be different among the multiple link mechanisms 30 .

Second Embodiment
Next, a second embodiment of the rotary machine according to the present invention will be described. In the second embodiment described below, in addition to the configuration of the first embodiment, the link mechanism 30 is provided with a dynamic vibration reducer 41. Therefore, the same parts as those in the first embodiment are denoted by the same reference numerals and will not be described again.

As shown in FIG. 6, the inlet guide vane portion 20B of the compressor 10 in this embodiment is provided with a plurality of link mechanisms 30. Of the plurality of link mechanisms 30, at least two of the link mechanisms 30 have different structures. In this embodiment, each of the plurality of link mechanisms 30 is provided with a dynamic vibration absorber 41. Each dynamic vibration absorber 41 has a mass body 42 and an elastic body 43. The mass body 42 is attached to the link mechanism 30 via the elastic body 43. The dynamic vibration absorber 41 is attached to, for example, the second link piece 34.

In this embodiment, at least two of the multiple link mechanisms 30 have different masses of the mass body 42 of the dynamic vibration absorber 41. In this embodiment, the multiple link mechanisms 30 are arranged such that link mechanism 30C having a large mass body 42A and link mechanism 30D having a small mass body 42B are alternately arranged in the circumferential direction Dc. The mass of the large mass body 42A is greater than the mass of the small mass body 42B. As a result, link mechanism 30C having large mass body 42A and link mechanism 30D having small mass body 42B have different natural frequencies and therefore different vibration characteristics.

(Action and Effect)
In the compressor 10 of the above embodiment, at least two of the multiple link mechanisms 30 are provided with dynamic vibration absorbers 41, which make the natural frequencies of the link mechanisms 30 different from each other. This makes it possible to make the vibration characteristics of the at least two link mechanisms 30 different. As a result, the inlet guide vane section 20B generates an imbalance in vibration characteristics in the multiple movable vanes 22 and link mechanisms 30 arranged in the circumferential direction Dc. This makes it possible to suppress the occurrence of unstable vibrations such as flutter in the inlet guide vane section 20B even under high load conditions where the flow velocity of the working fluid is high. As a result, it becomes possible to effectively suppress the vibration of the inlet guide vane.

(Modification of the second embodiment)
In the above embodiment, the masses of the mass bodies 42 of the dynamic vibration absorbers 41 are made different among the multiple link mechanisms 30. However, this is not limited to this. For example, the elastic coefficients of the elastic bodies 43 of the dynamic vibration absorbers 41 may be made different.
In addition, by providing link mechanisms 30 each having a dynamic vibration reducer 41 and link mechanisms 30 each not having a dynamic vibration reducer 41, the vibration characteristics of the multiple link mechanisms 30 may be made different.

Other Embodiments
Although the embodiments of the present disclosure have been described in detail above with reference to the drawings, the specific configuration is not limited to this embodiment, and design changes and the like that do not depart from the gist of the present disclosure are also included.
For example, as shown in Fig. 7, the inlet guide wing section 20C may be configured to include a damping material 51 as a damping mechanism 50A in each of the multiple link mechanisms 30. The damping material 51 is interposed between the pin insertion hole 31h formed in the link piece 31 and the pin 32 inserted into the pin insertion hole 31h. The damping material 51 damps the relative displacement caused by vibration between the link piece 31 and the pin 32. In the multiple link mechanisms 30, the damping characteristics of the damping material 51 sandwiched between the link piece 31 and the pin 32 may be made different, so that the vibration characteristics of the multiple link mechanisms 30 are made different. In addition, the multiple link mechanisms 30 may be configured to have different vibration characteristics by including a link mechanism 30 including the damping material 51 and a link mechanism 30 not including the damping material 51.

Also, for example, as shown in FIG. 8, each of the multiple link mechanisms 30 may be provided with a piezoelectric element 52 as a damping mechanism 50B. The piezoelectric element 52 is, for example, attached to the link piece 31. The piezoelectric element 52 damps the vibration by converting the vibration generated in the link piece 31 into electrical energy. The multiple link mechanisms 30 may have different vibration characteristics by differentiating the damping characteristics of the vibration caused by the piezoelectric element 52. The multiple link mechanisms 30 may have different vibration characteristics by providing a link mechanism 30 with a piezoelectric element 52 and a link mechanism 30 without a piezoelectric element 52.

Each of the multiple link mechanisms 30 may be provided with a collision damper as a damping mechanism. The collision damper may be, for example, a gas damper or an oil damper. The collision damper damps the vibration by damping the displacement of the first link piece 33 and the second link piece 34 that constitute the link mechanism 30. The vibration damping characteristics of the multiple link mechanisms 30 may be made different by making the vibration damping characteristics of the collision dampers different in the multiple link mechanisms 30. The vibration characteristics of the multiple link mechanisms 30 may be made different by providing a link mechanism 30 with a collision damper and a link mechanism 30 without a collision damper 53.

Alternatively, the contact areas between the link pieces 31 and the pins 32 may be made different to make the vibration damping characteristics of the multiple link mechanisms 30 different.
In addition, a vibration damping alloy may be used for the link pieces 31 and pins 32 that constitute the multiple link mechanisms 30, thereby improving the vibration damping characteristics of the link mechanisms 30.

<Additional Notes>
The rotating machine 10 according to the embodiment can be understood, for example, as follows.

(1) A rotary machine 10 according to a first aspect includes a rotor 11 including a rotor shaft 12 rotating about an axis Ar and a row of moving blades 13 fixed to the rotor shaft 12, a casing 15 covering the rotor 11, and inlet guide vane sections 20A to 20D arranged inside the casing 15 on a first side Da1 of an axial direction Da in which the axis Ar extends relative to the row of moving blades 13. The inlet guide vane sections 20A to 20D include a plurality of movable vanes 22 arranged at intervals in a circumferential direction Dc about the axis Ar and rotatable about a shaft section 24 extending in a radial direction Dr centered on the axis Ar. a drive ring 25 that is provided on the outer side Dro of the multiple movable blades 22 in the radial direction Dr, is continuous in the circumferential direction Dc, and is driven to displace in the circumferential direction Dc; and a plurality of link mechanisms 30, one link end 30a of which is connected to the shaft portion 24 of each of the multiple movable blades 22 and the other link end 30b of which is connected to the drive ring 25, so that when the drive ring 25 is displaced in the circumferential direction Dc, each of the multiple movable blades 22 rotates around the shaft portion 24, and at least two of the multiple link mechanisms 30 have different structures.
Examples of the rotary machine 10 include a compressor of a gas turbine, a centrifugal compressor, and a turbocharger.

This rotary machine 10 is equipped with multiple link mechanisms 30 that connect each of the multiple movable vanes 22 constituting the inlet guide vane sections 20A-20D to the drive ring 25. At least two of the multiple link mechanisms 30 have different structures. Link mechanisms 30 with different structures have different vibration characteristics. For this reason, the inlet guide vane sections 20A-20D have an imbalance in vibration characteristics in the multiple movable vanes 22 and link mechanisms 30 arranged in the circumferential direction Dc. This makes it possible to suppress unstable vibrations such as flutter in the inlet guide vane sections 20A-20D even under high-load conditions where the flow rate of the working fluid is high. As a result, it becomes possible to effectively suppress the vibration of the inlet guide vanes.

(2) The rotating machine 10 according to the second aspect is the rotating machine 10 according to (1), and each of the link mechanisms 30 includes a plurality of link pieces 31 arranged between the one link end 30a and the other link end 30b, and a pin 32 that connects the link pieces 31 to each other so that they can rotate freely.

As a result, in multiple link mechanisms 30 each having multiple link pieces 31 and pins 32, the vibration characteristics of at least two of the multiple link mechanisms 30 can be made different by varying the link pieces 31 and pins 32.

(3) The rotating machine 10 according to the third aspect is the rotating machine 10 according to (2), in which at least two of the multiple link mechanisms 30 differ from each other in at least one of the weight, rigidity, and dimension of the link piece 31 and/or the pin 32.

This allows the vibration characteristics of at least two link mechanisms 30 to be different by making at least one of the weight, rigidity, and dimensions of the link piece 31 and/or the pin 32 different.

(4) The rotating machine 10 according to the fourth aspect is the rotating machine 10 according to (2) or (3), in which at least two of the plurality of link mechanisms 30 are equipped with a dynamic vibration reducer 41, and thus have different natural frequencies.

As a result, at least two of the multiple link mechanisms 30 have different natural frequencies due to the dynamic vibration absorber 41. This makes it possible to make the vibration characteristics of at least two of the multiple link mechanisms 30 different.

(5) A rotating machine 10 according to a fifth aspect is any one of the rotating machines 10 of (1) to (4), wherein the plurality of link mechanisms 30 each include a damping mechanism 50A, 50B that damps vibrations generated in the link mechanism 30, and at least two of the plurality of link mechanisms 30 have damping characteristics in the damping mechanisms 50A, 50B that are different from each other.
The damping mechanisms 50A and 50B include a damping material 51, a piezoelectric element 52, and a collision damper.

As a result, by differentiating the damping characteristics of the damping mechanisms 50A and 50B, it is possible to differentiate the vibration characteristics of at least two of the multiple link mechanisms 30.

1... Gas turbine 2... Combustor 3... Turbine 10... Compressor (rotary machine)
11... rotor 12... rotor shaft 13, 13A... moving blade row 15... casing 17... stator blade row 20A, 20B... inlet guide vane portion 21... frame 21h... blade retaining hole 22... movable blade 23... blade body 23a... one end 23b... other end 24... shaft portion 24s... tip portion 25... drive ring 26... center hub 26a... blade retaining recess 30, 30A to 30D... link mechanism 30a... one link end 30b... other link end 31... link piece 32... pin 32A... large diameter pin 3 2B...Small diameter pin 33...First link piece 33a...One end 33b...Other end 33h...Pin insertion hole 34...Second link piece 34a...One end 34b...Other end 35...First pin 36...Second pin 41...Dynamic vibration absorber 42...Mass body 42A...Large mass body 42B...Small mass body 43...Elastic body 50A, 50B...Damping mechanism 51...Damping material 52...Piezoelectric element Ar...Axis Cs...Central axis Da...Axial direction Da1...First side Da2...Second side Dc...Circumferential direction Dr...Radial direction Dri...Inner side Dro...Outer side

Claims (4)

A rotor including a rotor shaft that rotates about an axis and a row of rotor blades fixed to the rotor shaft;
A casing that covers the rotor;
an inlet guide vane portion disposed inside the casing on a first side in an axial direction in which the axis extends relative to the rotor blade row;
The inlet guide vane portion is
A plurality of movable blades are arranged at intervals in a circumferential direction around the axis line and are rotatable around a shaft portion extending in a radial direction centered on the axis line;
a drive ring provided radially outward of the plurality of movable blades, continuous in the circumferential direction, and driven to be displaced in the circumferential direction;
a plurality of link mechanisms, each having one link end connected to the shaft portion of each of the plurality of movable blades and the other link end connected to the drive ring, for rotating each of the plurality of movable blades around the shaft portion when the drive ring is displaced in the circumferential direction;
Each of the plurality of link mechanisms includes:
a plurality of link pieces disposed between the one link end and the other link end;
a pin that rotatably connects the plurality of link pieces to each other,
At least two of the link mechanisms are provided with dynamic vibration absorbers, so that the natural frequencies of the link mechanisms are different from each other.
Rotating machinery. At least two of the link mechanisms among the plurality of link mechanisms include
The rotary machine according to claim 1 , wherein at least one of the link pieces and the pins differ from each other in at least one of weight, stiffness, and size. Each of the plurality of link mechanisms includes:
a damping mechanism for damping vibrations generated in the link mechanism,
At least two of the link mechanisms among the plurality of link mechanisms include
The rotating machine according to claim 1 or 2, wherein the damping mechanisms have different damping characteristics.
A rotor including a rotor shaft that rotates about an axis and a row of rotor blades fixed to the rotor shaft;
A casing that covers the rotor;
an inlet guide vane portion disposed inside the casing on a first side in an axial direction in which the axis extends relative to the rotor blade row;
The inlet guide vane portion is
A plurality of movable blades are arranged at intervals in a circumferential direction around the axis line and are rotatable around a shaft portion extending in a radial direction centered on the axis line;
a drive ring provided radially outward of the plurality of movable blades, continuous in the circumferential direction, and driven to be displaced in the circumferential direction;
a plurality of link mechanisms, each having one link end connected to the shaft portion of each of the plurality of movable blades and the other link end connected to the drive ring, for rotating each of the plurality of movable blades around the shaft portion when the drive ring is displaced in the circumferential direction;
Each of the plurality of link mechanisms includes:
a damping mechanism for damping vibrations generated in the link mechanism,
At least two of the link mechanisms among the plurality of link mechanisms include
A rotating machine in which the damping mechanisms have different damping characteristics.

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