JP2010236387A - Stationary blade variable device and axial flow type fluid machine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a stationary blade variable device changing blade angle of each blade even if distance between stationary blade stages is small. <P>SOLUTION: This stationary blade variable device 100 includes blade axes 110 extending radial direction outward from the plurality of stationary blades disposed in an annular shape around a center axis line with predetermined intervals, a blade ring 43 supporting the blade axes 110 rotatably around axial lines thereof, an annular variable ring 130 disposed rotatably around the center axis line, and a rotation mechanism 150 rotating the variable ring 130 around the center axis line. A plurality of stationary blade stages comprising the plurality of stationary blades disposed in an annular shape are disposed in a direction along the center axis line. A link mechanism converting rotation of the variable ring 130 by the rotation mechanism 150 to rotation around the axial line of the blade axis 110 and transmitting the same over the plurality of stationary blade stages is provided. <P>COPYRIGHT: (C)2011,JPO&amp;INPIT

Description

  The present invention relates to a stationary blade variable device that changes the blade angle of a stationary blade, and an axial-flow fluid machine including the same.

  The axial flow compressor includes a plurality of stationary blade stages in which a large number of stationary blades are arranged in an annular shape and a moving blade stage in which a large number of moving blades are attached to a rotating shaft. Among such axial flow compressors, one having a stationary blade variable device that changes the blade angle of each stationary blade in accordance with the operating state is known (for example, see Patent Document 1).

  As shown in FIG. 4, the stationary blade variable mechanism is arranged outside the compressor casing so as to be concentric with the rotation shaft, and has an annular variable ring 230 that can rotate around the rotation shaft. Yes. As shown in FIG. 5A, the variable ring 230 is connected to an arm 220 attached to the shaft tip of each stationary blade. The variable ring 230 is connected to a movable shaft 252 via a crank 251 and is movable in the circumferential direction. By having such a structure, the movable shaft 252 is rotated to rotate the variable ring 230 around the rotation axis, thereby giving a swing angle to the arm 220 and causing the blade shaft connected to the arm 220 to rotate around its axis. Turn to. Thereby, as shown in FIG.5 (b), the blade angle of all the stationary blades is changed.

JP 2002-5096 A

  By the way, in order to raise the pressure of the fluid in a casing, it is necessary for an axial flow type compressor to make the distance between each stationary blade stage small as it approaches a back stage (exit side). However, according to the axial flow compressor disclosed in Patent Document 1, each stationary blade stage and the variable ring have a one-to-one structure. There is an inconvenience that the installation space is narrowed and the disassembly / assembly work is hindered.

  Further, in the remodeling work in which the number of stages is increased for the purpose of increasing the capacity or the like, there is a restriction on the space for adding the parts, so it is necessary to reduce the distance between each stationary blade stage. In this case, in particular, there is an inconvenience that it becomes difficult to install the variable ring because the distance between the rear stationary blade stages becomes too small.

  The present invention has been made in view of the above circumstances, and even when the distance between the stationary blade stages is small, the stationary blade variable device capable of changing the blade angle of each stationary blade and the axial flow type equipped with the same. An object is to provide a fluid machine.

In order to solve the above problems, the present invention employs the following means.
According to a first aspect of the present invention, there is provided a blade shaft extending radially outward from each of a plurality of stationary blades arranged annularly around a central axis at predetermined intervals, and the blade shafts about the axis. A support member that is rotatably supported; an annular variable ring that is rotatably disposed about the central axis; and a rotation mechanism that rotates the variable ring about the central axis. A plurality of vane stages composed of the plurality of vanes arranged in the center are provided in a direction along the central axis, and the rotation of the variable ring by the rotation mechanism is performed around the axis of the blade axis. It is a stationary blade variable device provided with a link mechanism that converts the motion into a plurality of stationary blade stages.

  According to the first aspect of the present invention, when the variable ring is rotated around the central axis of the ring by the rotation mechanism, the rotation of the variable ring is rotated around the axis of the blade axis by the link mechanism. Since it is converted, it is possible to change the blade angle of the stationary blade connected to the blade shaft by rotating the blade shaft around its axis. Here, in the first aspect of the present invention, a plurality of stationary blade stages each including a plurality of stationary blades arranged in an annular shape are provided in a direction along the central axis, and the variable ring rotates. And transmitted across a plurality of stationary blade stages by a link mechanism. Therefore, the blade angle of the stationary blades in the plurality of stationary blade stages can be changed by rotating one variable ring. As a result, the number of installations of the variable ring can be reduced, so that the installation space can be reduced, and the blade angle of the stationary blade can be changed even when the distance between the stationary blade stages is small. . Further, since the number of parts can be reduced, the manufacturing cost can be reduced.

  In the above aspect, the link mechanism connects the variable ring and the blade shaft, is connected to the variable ring so as to be rotatable, and is connected to an eccentric position of the blade shaft; A blade shaft coupled to the variable ring by the first coupling member and a blade shaft of a stationary blade stage adjacent to the blade shaft are coupled, and a second is rotatably connected to an eccentric position of the blade shaft. It is good also as having this connection member.

  By configuring the link mechanism in this way, when the variable ring is rotated around the central axis of the ring by the rotation mechanism, the rotation of the variable ring can be freely rotated to the variable ring by the first connecting member. It is transmitted to the connected blade axis, and a swing angle is given to the blade axis. Since the blade axis is rotated around the axis according to the given swing angle, the blade angle of the stationary blade attached to the blade axis is changed. Further, the rotation of the variable ring is transmitted to the blade shaft of the adjacent stationary blade stage by the second connecting member, and a swing angle is also given to the blade shaft, so that the stationary blade attached to the blade shaft is rotated. The wing angle is changed. In this way, by having the above-described configuration and forming a link mechanism and rotating one variable ring, the blade angles of the stationary blades in a plurality of stationary blade stages can be changed.

  In the above aspect, the rotation mechanism includes a crank connected to the variable ring and extending radially outward of the ring, a movable shaft connected to the crank, and a motor that rotationally drives the movable shaft. It is good as well.

  By configuring the turning mechanism in this way, the movable shaft can be rotationally driven by the motor, and the driving force can be transmitted to the variable ring via the crank. As a result, the variable ring can be rotated about the central axis, the blade shaft can be rotated about the axis, and the blade angle of the stationary blade can be changed.

  According to a second aspect of the present invention, a cylindrical casing, a rotating shaft rotatably supported inside the casing, a radially outwardly provided on the rotating shaft, and a predetermined interval in the circumferential direction. A plurality of moving blades arranged in an annular shape with a gap therebetween, a plurality of stationary blades provided in the casing inward in the radial direction and arranged in an annular shape with a predetermined interval in the circumferential direction, and And a stationary blade stage composed of the plurality of stationary blades arranged in an annular shape, and a stationary blade stage composed of the plurality of stationary blades arranged in an annular shape. Are axial flow type fluid machines provided in a plurality along the rotation axis.

  According to the second aspect of the present invention, since the above-described stator blade variable device is provided, the blade angle of each stator blade can be changed according to the operating state, so that the capability can be improved. At the same time, the manufacturing cost can be reduced by downsizing the machine body.

  According to the present invention, it is possible to change the blade angle of each stationary blade even when the distance between the blade stages is small.

It is a schematic block diagram of the BFG-fired gas turbine equipment provided with the axial flow compressor which concerns on one Embodiment of this invention. It is a longitudinal cross-sectional view of the axial flow type compressor of FIG. It is the elements on larger scale of the stator blade variable apparatus of FIG. 2, (a) is the longitudinal cross-sectional view of the axial direction of a blade axis | shaft, (b) is the cross-sectional view of the axial direction of a blade axis | shaft. It is a cross-sectional view of a variable ring in a conventional axial compressor. It is the elements on larger scale of the conventional stationary blade variable apparatus, (a) is the longitudinal cross-sectional view of the axial direction of a blade axis | shaft, (b) is a cross-sectional view of the axial direction of a wing shaft.

Hereinafter, an embodiment of a stationary blade variable device according to the present invention and an axial flow type fluid machine including the same will be described with reference to the drawings.
In this embodiment, as an example of an axial flow type fluid machine, an axial flow type compressor that compresses fuel gas in a BFG-fired gas turbine facility that uses blast furnace gas (hereinafter referred to as “BFG”) as fuel gas. A case where the present invention is applied to will be described.

FIG. 1 is a schematic configuration diagram for explaining an outline of a BFG-fired gas turbine facility provided with an axial compressor according to the present embodiment.
In general, the supply pressure of BFG depends on the operating pressure of the blast furnace, and the pressure is low for use as the combustion gas of the gas turbine 2 in the BFG-fired gas turbine facility 1. Therefore, as shown in FIG. 1, in addition to the gas turbine 2, a compressor such as an axial flow compressor 4 that compresses the blast furnace gas and raises the pressure to a predetermined pressure is used.

As shown in FIG. 1, the BFG-fired gas turbine facility 1 includes a gas turbine 2, a generator 3, and an axial compressor 4 as main components.
The gas turbine 2 is a gas turbine that is operated using the BFG compressed by the axial flow compressor 4 as a fuel gas, and rotates the generator 3.
The gas turbine 2 is provided with a gas turbine compressor 21, a combustor 22, a turbine unit 23, and a gas turbine rotating shaft 24.

  The gas turbine compressor 21 compresses air taken from the outside, and supplies the compressed air to the combustor 22. Further, the gas turbine compressor 21 is connected to a gas turbine rotating shaft 24 and is configured to compress air by being rotationally driven by the gas turbine rotating shaft 24.

  The combustor 22 burns an air-fuel mixture of air compressed by the gas turbine compressor 21 and BFG compressed by the axial flow compressor 4, and the high-temperature combustion gas generated by the combustion is converted into a turbine. It supplies to the part 23.

  The turbine unit 23 converts the energy of the combustion gas supplied from the combustor 22 into a rotational driving force. Further, the turbine unit 23 is configured to be able to transmit the rotational driving force to the gas turbine rotating shaft 24.

  The gas turbine rotating shaft 24 is a cylindrical member connected to the turbine unit 23, the gas turbine compressor 21, and the generator 3, and the rotational driving force is supplied from the turbine unit 23 to the gas turbine compressor 21 and the generator 3. To communicate.

  In addition, a well-known structure can be used as the structure which concerns on the gas turbine 2, for example, the gas turbine compressor 21, the combustor 22, the turbine part 23, and the gas turbine rotating shaft 24, It does not specifically limit. .

  The generator 3 is driven to rotate by the gas turbine 2 to generate power. A gas turbine rotating shaft 24 is connected to the generator 3 so that the rotational driving force of the gas turbine rotating shaft 24 is transmitted. In addition, as the generator 3, a well-known thing can be used and it does not specifically limit.

The axial compressor 4 compresses BFG and supplies it to the gas turbine 2. The axial flow compressor 4 is provided with a compressor rotation shaft (rotation shaft) 41 to which a rotational driving force is transmitted from the gas turbine rotation shaft 24.
In the present embodiment, an example in which the speed increasing portion 41G is disposed between the gas turbine rotating shaft 24 and the compressor rotating shaft 41 will be described, but the speed increasing portion 41G may not be disposed. Well, not particularly limited.

FIG. 2 is a longitudinal sectional view for explaining the configuration of the axial flow compressor 4 of FIG.
As shown in FIG. 2, the axial flow compressor 4 includes a compressor rotating shaft 41, a casing 42, a blade ring (casing) 43, a plurality of moving blades RB and stationary blades SV, and a stationary blade variable device. 100 as main components. A flow path 44 is formed between the blade ring 43 and the compressor rotation shaft 41.

  The casing 42 accommodates therein a compressor rotating shaft 41, a blade ring 43, a flow path 44, a moving blade RB, a stationary blade SV, a stationary blade variable device 100, and the like. Further, the casing 42 supports the blade ring 43 to support the stationary blade SV, the stationary blade variable device 100, and the like attached to the blade ring 43.

  The blade ring 43 is a member formed in a substantially cylindrical shape, and rotatably supports the compressor rotating shaft 41 disposed radially inward, and houses the moving blade RB and the stationary blade SV therein. Yes. The blade ring 43 is provided with a plurality of holes through which a blade shaft 110, which will be described later, penetrates. A support member such as a bearing that rotatably supports the blade shaft 110 about its axis is provided in the hole. It has been.

  The flow path 44 is a cylindrical flow path formed between the blade ring 43 and the compressor rotation shaft 41. From the upstream side toward the downstream side (from the left side to the right side in FIG. 2), the BFG It is formed so that the cross-sectional area of the flow path through which the gas flows is reduced.

  The moving blade RB and the stationary blade SV are blades arranged in an annular shape in the flow path 44, and are used for compression of BFG. The rotor blades RB and the stationary blades SV arranged in an annular shape form one stage as a pair. Here, a 20-stage axial flow compressor 4 will be described as an example.

  The moving blades RB are blades that are arranged on the outer peripheral surface of the compressor rotation shaft 41 at equal intervals in the circumferential direction and extend outward in the radial direction. The rotor blade RB is configured to compress the BFG passing through the stage together with the stationary blade SV belonging to the same stage by being rotationally driven integrally with the compressor rotating shaft 41.

The stationary blades SV are blades that are arranged on the inner peripheral surface of the blade ring 43 at equal intervals in the circumferential direction and extend inward in the radial direction. Here, the vane angle of the 17th vane SV17 to the 20th vane SV20 arranged at the rear stage (the right stage in FIG. 2) can be changed by the vane variable device 100. And
In the present embodiment, as shown in FIG. 2, a blade shaft 110A is provided on the stationary blade SV17, a blade shaft 110B on the stationary blade SV18, a blade shaft 110C on the stationary blade SV19, and a blade shaft 110D on the stationary blade SV20. .

3 (a) and 3 (b) are partial enlarged views for explaining the configuration of the stationary blade variable device 100 of FIG. 2, (a) is a longitudinal sectional view in the axial direction of the blade shaft 110, and (b). FIG. 3 is a cross-sectional view of the blade shaft 110 in the axial direction.
The stator blade variable device 100 changes the blade angle of the stator blade SV17 to the stator blade SV20. As shown in FIG. 3A, the blade shaft 110 connected to the stator blade SV and the arm (first ) 120, an arm 121, a connecting arm (second connecting member) 125, an annular variable ring 130 that is rotatable around the central axis of the compressor rotating shaft 41, and holds these members. A holding ring 140 that rotates, and a rotation mechanism 150 that rotates the variable ring 130. Arms 120A and 120B are collectively referred to as arm 120, arms 121A and 121B are collectively referred to as arm 121, and connection arms 125A and 125B are collectively referred to as connection arm 125.

  Blade axis 110 is a cylindrical member extending radially outward from each of a plurality of stationary blades SV arranged in an annular shape. The blade shaft 110 is supported by the blade ring 43 so as to be rotatable about the axis of the blade shaft 110.

The arm 120 and the arm 121 transmit the rotation of the variable ring 130 to the blade shaft 110, and are rod-shaped members extending from the radially outer end of the blade shaft 110.
In this embodiment, as shown in FIGS. 3 (a) and 3 (b), the blade 120A has an arm 120A, the blade shaft 110B has an arm 121A, the blade shaft 110C has an arm 120B, and the blade shaft 110D has an arm 121B. Is provided.

  As shown in FIG. 3B, the arm 120A has one end fixed to the blade shaft 110A and the other end rotatably connected to the variable ring 130A via a pin. The arm 120B has one end fixed to the blade shaft 110C and the other end rotatably connected to the variable ring 130B via a pin.

  The connecting arm 125 connects the arm 120 and the arm 121 and transmits the rotation of the variable ring 130 to the blade shaft 110. Specifically, the connecting arm 125 is provided with pins at both ends, and rotates the blade shaft 110 connected to the variable ring 130 by the arm 120 and the blade shaft 110 of the stationary blade stage adjacent to the blade shaft 110. It is designed to be freely connected. That is, in this embodiment, the connecting arm 125A rotatably connects the arm 120A and the arm 121A at the eccentric position of each blade shaft 110, and the connecting arm 125B allows the arm 120B and the arm 121B to rotate freely. To be connected to.

  As described above, a link mechanism is formed by connecting the variable ring 130 and the blade shaft 110, and the rotation of the variable ring 130 by the rotation mechanism 150 is converted into the rotation of the blade shaft 110. Is transmitted across the stationary blade stage.

  The variable ring 130 is an annular member disposed concentrically with the compressor rotation shaft 41, and is supported by the holding ring 140 so as to be rotatable around the central axis of the compressor rotation shaft 41. In the present embodiment, as shown in FIG. 3A, a variable ring 130A and a variable ring 130B are provided.

The rotation mechanism 150 includes a crank 151 connected to the variable ring 130 and extending radially outward, a movable shaft 152 connected to the crank 151, and a motor 153 that rotationally drives the movable shaft 152. The cranks 151A and 151B are collectively referred to as a crank 151.
In the present embodiment, as shown in FIG. 3A, a crank 151A is connected to the variable ring 130A, and a crank 151B is connected to the variable ring 130B.

  By configuring the rotation mechanism 150 in this way, the movable shaft 152 can be rotationally driven by the motor 153 and the driving force can be transmitted to the variable ring 130 via the crank 151. Thereby, the variable ring 130 can be rotated around the central axis of the compressor rotating shaft 41.

  The holding ring 140 holds the variable ring 130 through the collar 132 and the roller 141 in a rotatable manner. The holding ring 140 is formed in a substantially cylindrical shape at the center, and is arranged so as to cover the blade shaft 110, the arm 120, and the variable ring 130 from the outside in the radial direction.

The operation of the BFG-fired gas turbine equipment 1 including the axial compressor 4 having the above configuration will be described below with reference to FIG.
BFG supplied from the blast furnace is sucked into the axial compressor 4 as shown in FIG. The axial flow compressor 4 is driven by the rotational driving force transmitted to the compressor rotation shaft 41 via the gas turbine rotation shaft 24, and boosts the BFG to a predetermined pressure.
The boosted BFG is supplied from the axial compressor 4 to the combustor 22 of the gas turbine 2.

On the other hand, the gas turbine compressor 21 is driven to rotate by the gas turbine rotating shaft 24, thereby sucking outside air and increasing the pressure to a predetermined pressure.
The pressurized air is supplied from the gas turbine compressor 21 to the combustor 22.

In the combustor 22, the air-fuel mixture of the pressurized BFG and the pressurized air is combusted, and high-temperature combustion gas is generated. The combustion gas is supplied from the combustor 22 to the turbine unit 23.
In the turbine part 23, the thermal energy etc. which combustion gas has are converted into rotational drive force. The rotational driving force is transmitted from the turbine unit 23 to the gas turbine rotating shaft 24. The combustion gas is then discharged from the turbine unit 23.

The gas turbine rotating shaft 24 transmits rotational driving force to the gas turbine compressor 21 and the generator 3, and rotationally drives the gas turbine compressor 21 and the generator 3. Thereby, the gas turbine compressor 21 compresses external air, and the generator 3 generates electric power.
On the other hand, the gas turbine rotating shaft 24 transmits the rotational driving force to the compressor rotating shaft 41 via the speed increasing portion 41G to drive the axial flow compressor 4.

Next, an operation when changing the blade angle of the stationary blade SV17 to the stationary blade SV20 in the axial flow compressor 4 will be described.
The blade angle of the stationary blade SV17 to the stationary blade SV20 is changed by rotating the variable ring 130 around the central axis of the compressor rotating shaft 41. Specifically, by rotating the movable shaft 152 by the motor 153, the cranks 151A and 151B are driven along the tangential direction of the variable rings 130A and 130B. The movement of the cranks 151A and 151B in the tangential direction is transmitted to the variable rings 130A and 130B and converted into rotation of the variable rings 130A and 130B.

  The rotation of the variable rings 130A and 130B is transmitted to the arms 120A and 120B rotatably connected to the variable rings 130A and 130B, and the arms 120A and 120B are moved to the variable ring 130A as shown in FIG. , 130B is rotated around the connection point (pin). The rotation of the arms 120A and 120B is transmitted to the blade shafts 110A and 110C fixed to the arms 120A and 120B, respectively, and a swing angle is given to the blade shafts 110A and 110C. Since the blade shafts 110A and 110C are supported by the blade ring 43 so as to be rotatable around the axis thereof, the blade shafts 110A and 110C are rotated around the axis line according to a given swing angle. As a result, the blade angles of the stationary blades SV17 and SV19 connected to the blade shafts 110A and 110C are changed.

  Further, the arms 120A and 120B are rotated, whereby the connecting arms 125A and 125B are pulled in a direction orthogonal to the axis of the blade shaft 110. As a result, the arms 121A and 121B rotatably connected to the connecting arms 125A and 125B are rotated. The rotation of the arms 121A and 121B is transmitted to the blade shafts 110B and 110D fixed to the arms 121A and 121B, and a swing angle is given to the blade shafts 110B and 110D. Since the blade shafts 110B and 110D are supported by the blade ring 43 so as to be rotatable around the axis thereof, the blade shafts 110B and 110D are rotated around the axis line according to a given swing angle. Thereby, the blade angles of the stationary blades SV18 and SV20 connected to the blade shafts 110B and 110D are changed.

  As described above, according to the stator blade variable device 100 according to the present embodiment, when the variable rings 130A and 130B are rotated around the central axis of the compressor rotation shaft 41 by the rotation mechanism 150, the variable rings 130A and 130A are rotated. The rotation of the variable rings 130A and 130B is converted into the rotation of the blade shafts 110A and 110C by the arms 120A and 120B rotatably connected to the 130B. As a result, the blade shafts 110A and 110C can be rotated about the axis thereof, and the blade angles of the stationary blades SV17 and SV19 connected to the blade shafts 110A and 110C can be changed.

  Further, according to the stationary blade variable device 100 according to the present embodiment, the rotation of the blade shafts 110A and 110C (arms 120A and 120B) is performed via the connecting arms 125A and 125B, and the blade shaft 110B of the adjacent stationary blade stage. , 110D. Accordingly, the blade angles of the stationary blades SV17 and SV19 connected to the blade shafts 110B and 110D can be changed by rotating the variable rings 130A and 130B around the central axis of the compressor rotation shaft 41.

  That is, according to the stationary blade variable device 100 according to the present embodiment, the blade angle of the stationary blades (for example, SV17 and SV18) in a plurality of stationary blade stages is obtained by rotating one variable ring (for example, the variable ring 130A). Can be changed. Thereby, since the number of installation of the variable ring 130 can be reduced, the installation space can be reduced, and even when the distance between the stationary blade stages is small, the blade angle of the stationary blade SV can be changed. It becomes. Further, since the number of parts can be reduced, the manufacturing cost can be reduced.

  Further, according to the axial flow compressor 4 according to the present embodiment, since the stator blade variable device 100 is provided, the blade angle of the stator blade SV can be changed according to the operating state. It is possible to improve the capacity such as the discharge pressure and the discharge flow rate, and to reduce the manufacturing cost by reducing the size of the machine body.

As mentioned above, although embodiment of this invention was explained in full detail with reference to drawings, the specific structure is not restricted to this embodiment, The design change etc. of the range which does not deviate from the summary of this invention are included.
For example, in the present embodiment, taking a 20-stage axial flow compressor as an example, the blade angle of the stationary blade SV in four stages is changed, but the blade of the stationary blade SV having three or less stages or five or more stages is used. The present invention can be applied even when the corner is changed, and is not limited to this example.

  Further, in the present embodiment, it has been described that the two stationary blade stages are connected by the connecting arm 125, but three or more adjacent stationary blade stages may be connected to form a link mechanism.

  In the present embodiment, the present invention is applied to the axial flow compressor 4 that compresses the fuel gas in the BFG-fired gas turbine facility 1. However, the shaft that compresses another fluid used in other facilities. You may apply to a flow type compressor. Furthermore, you may apply to axial flow type fluid machines, such as an axial flow type blower which has the same structure.

4 Axial-flow compressors 41 Compressor rotating shaft (rotating shaft)
43 Wing ring (casing)
RB Rotor blade SV, SV17, SV18, SV19, SV20 Stator blade 100 Stator blade variable device 110, 110A, 110B, 110C, 110D Blade shaft 120A, 120B Arm (first connecting member)
121A, 121B Arm 125A, 125B Connecting arm (second connecting member)
130, 130A, 130B Variable ring 150 Rotating mechanism 151A, 151B Crank 152 Movable shaft 153 Motor

Claims (4)

A blade axis extending radially outward from each of a plurality of stationary blades arranged in a ring around the central axis at a predetermined interval;
A support member that rotatably supports these blade axes around the axis, and
An annular variable ring disposed so as to be rotatable around the central axis;
A rotation mechanism for rotating the variable ring around the central axis,
A plurality of vane stages composed of the plurality of vanes arranged in an annular shape are provided in a direction along the central axis,
A stator blade variable device provided with a link mechanism that converts the rotation of the variable ring by the rotation mechanism into rotation around the axis of the blade shaft and transmits the rotation to the plurality of stator blade stages. The link mechanism is
A first connecting member that connects the variable ring and the blade shaft, is pivotally connected to the variable ring, and is connected to an eccentric position of the blade shaft;
A blade shaft coupled to the variable ring by the first coupling member and a blade shaft of a stationary blade stage adjacent to the blade shaft are coupled, and a second is rotatably connected to an eccentric position of the blade shaft. The stator blade varying device according to claim 1, further comprising: a connecting member. The rotation mechanism is
A crank connected to the variable ring and extending radially outward of the ring;
A movable shaft connected to the crank;
The stationary blade variable device according to claim 1, further comprising a motor that rotationally drives the movable shaft. A cylindrical casing;
A rotating shaft rotatably supported in the casing;
A plurality of rotor blades provided radially outward on the rotating shaft and arranged in an annular shape at predetermined intervals in the circumferential direction;
A plurality of stationary blades provided in the casing inward in the radial direction and arranged in an annular shape with a predetermined interval in the circumferential direction;
A stator blade variable device according to any one of claims 1 to 3,
A plurality of moving blade stages composed of the plurality of moving blades arranged in an annular shape and a plurality of stationary blade stages composed of the plurality of stationary blades arranged in an annular shape are provided in a direction along the rotation axis. Axial flow type fluid machine.

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