JP2002005096A - Axial flow compressor and gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an axial flow compressor and a gas turbine which maintain the constant setting angle of each stationary blade composing the stationary blade row irrespective of thermal expansion of compressor casing, and exert constant performance with high reliability even with low load, etc. SOLUTION: The axial flow compressor AC composing the gas turbine GT is equipped with the stationary blade row CSC installed inside the compressor casing 3 and the rotor blade row CRC installed on the main shaft 17, and is able to changed with the setting angle of each of compressor stationary blades CS2-CS5 composing the stationary blade row CSC consisting of 2nd to 5th rows. This compressor AC is connected with each of compressor stationary blades CS2-CS5 and supported by variable rings 42R-45R which rotate around the main shaft 17 and also supported by the compressor casing 3 allowing both expansion and shrinkage along the diameter of main shaft 17. This compressor is also equipped with the supporting ring 50 which supports each of variable rings 42R-45R by rotating flexibly.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial compressor capable of changing the mounting angle of each vane constituting a vane row.
Further, the present invention relates to a gas turbine provided with such an axial compressor.

[0002]

2. Description of the Related Art Technologies belonging to such fields include:
One disclosed in Japanese Patent Application Laid-Open No. Hei 7-317501 is known. The conventional axial-flow compressor described in this publication includes a large number of stages each including a stationary blade row and a moving blade row, and changes the mounting angle of a large number of stationary blades constituting each stage of the stationary blade row. Can be done. The variable vane mechanism provided in this axial flow compressor includes a cylindrical variable ring disposed around the compressor casing so as to be concentric with the main shaft. A plurality of guide grooves are formed on the inner peripheral surface of the variable ring so as to correspond to each row of stationary blade rows. In addition, the shaft of the vane of each stage is provided on an arm having a roller at the tip, and the roller of each arm engages with the guide groove of the variable ring.

On the other hand, spiral tracks are laid at four locations on the outer peripheral surface of the variable ring, and each track engages with a spiral groove formed on a bracket fixed to a compressor casing. Further, the axial flow compressor is provided with an electric actuator and a gear mechanism for rotating the variable ring around the main shaft. When the electric actuator is operated, the variable ring rotates around the main shaft and moves in the extending direction (axial direction) of the main shaft while being guided by the orbit and the spiral groove. Thus, the mounting angle of each vane changes according to the amount of movement of the variable ring.

[0004]

Generally, when the axial compressor is operated, the temperature of the casing rises due to the rise in the temperature of the fluid to be handled, and the casing expands. On the other hand, since the variable ring is provided around the casing and is not affected by the temperature rise of the handled fluid as much as the casing, the degree of expansion is smaller than that of the casing. Therefore, in order to improve the performance at the rated point, the variable ring is attached to the casing with a certain amount of backlash in the radial direction of the main shaft being provided in advance, particularly in the downstream stage, based on the thermal expansion of the casing. There is a need.

However, due to the provision of such play, the variable ring falls due to its own weight before or immediately after the start of operation of the axial compressor, that is, when the thermal expansion of the casing is small. Will be. In this case, the axis of the variable ring deviates from the axis of the main shaft (casing), and the mounting angle of each of the stationary blades forming one stationary blade row varies (inclined). When the axial compressor is operated in this state, surging occurs at a low load, and in some cases, the stationary blade or the moving blade may be damaged.

Accordingly, the present invention can maintain a fixed mounting angle of each of the stationary blades constituting one stationary blade row irrespective of the thermal expansion of the casing, and can exhibit stable performance even at a low load. Another object of the present invention is to provide an axial compressor having high reliability and a gas turbine including such an axial compressor.

[0007]

According to the first aspect of the present invention, there is provided an axial compressor having a stationary blade row provided in a casing and a moving blade row attached to a main shaft. In an axial flow compressor that can change the mounting angle of each vane constituting a row, a variable ring that is linked to each vane and can rotate around the main shaft, and expands and contracts in the radial direction of the main shaft A support ring rotatably supported by the casing and rotatably supporting the variable ring.

In this axial flow compressor, the variable ring is linked to each of the stationary blades constituting one row of stationary blades via an arm, a connecting pin, and the like, and is rotatably supported by a support ring.
The support ring is arranged, for example, so as to cover the outer periphery of the casing, and is supported by the casing so as to be able to expand and contract in the radial direction of the main shaft. This makes it possible to arrange the variable ring and the support ring away from the casing, while maintaining the temperature of the variable ring and the support ring lower than the casing temperature, such as during operation of the axial compressor. The temperature difference between the two can be reduced.

As a result, the difference in the amount of thermal expansion and contraction between the variable ring and the support ring can be reduced, so that during operation of the axial-flow compressor, the variable ring is moved to the same degree as the support ring. (Main axis).
This makes it possible to minimize the play between the support ring and the variable ring when supporting the variable ring, and always keeps the variable ring concentric with the main shaft (casing) regardless of the thermal expansion of the casing. Can be maintained. Therefore, in this axial flow compressor, even at the time of low load or the like, the mounting angle of each of the stator blades constituting one stator blade row can be maintained substantially constant,
It is possible to prevent occurrence of surging at the time of low load or the like and damage to the stationary blade and the moving blade.

It is preferable that guide members extending in the radial direction of the main shaft, fixed to one of the support ring and the casing, and slidable with respect to the other are provided at at least three places. .

With this configuration, the supporting ring can be easily and reliably supported on the casing so as to be able to expand and contract, and the expanding and contracting supporting ring can be surely concentric with the casing (main shaft). Can be maintained.

Further, the support ring may be formed of a high thermal expansion material.

Such a structure is particularly effective when, for example, the support ring is arranged on the outer periphery of the casing and the variable ring is supported on the inner periphery of the support ring. In other words, in such a configuration, the variable ring is located closer to the casing than the support ring, and thus the temperature is easily increased by the influence of the casing temperature. Therefore, if the support ring is formed of a high thermal expansion material, the difference in the amount of thermal expansion between the variable ring and the support ring can be similarly maintained regardless of the casing temperature. This makes it possible to minimize the play between the variable ring and the support ring when the variable ring is supported by the support ring, and always keeps the variable ring concentric with the main shaft (casing) regardless of the degree of thermal expansion of the casing. Can be maintained.

It is preferable that the apparatus further comprises a ring temperature adjusting means for reducing a difference between the temperature of the variable ring and the temperature of the casing.

By adopting such a configuration, the temperature of the variable ring and the temperature of the casing can be maintained similarly, and the difference in the amount of thermal expansion between the two can be reduced. Therefore, the play between the variable ring and the casing can be minimized, and the variable ring can always be maintained concentric with the main shaft (casing). The support ring is expandable and contractible in the radial direction of the main shaft with respect to the casing, and follows the variable ring which expands and contracts so as to be concentric with the main shaft (casing).

In this case, it is preferable that the ring temperature adjusting means comprises a heat medium passage formed in a variable ring, and a heat medium supply pipe for guiding a handled fluid from the annular passage in the casing to the heat medium passage.

The ring temperature adjusting means includes an annular pipe provided around the variable ring and having a plurality of outlets, and a heat medium supply pipe for guiding a fluid to be handled from the annular flow path in the casing to the annular pipe. May be.

According to a seventh aspect of the present invention, there is provided a gas turbine in which a working fluid is pressurized by a compressor and burned by a combustor, and the working fluid whose temperature and pressure are increased is expanded by the turbine to generate power. The machine has a stationary blade row provided in the compressor casing, and a moving blade row attached to the main shaft, it is possible to change the mounting angle of each vane constituting the stationary blade row, A variable ring which is linked to each of the stationary blades and can be rotated around the main shaft; and a support ring which is supported by the casing so as to be expandable and contractible in the radial direction of the main shaft and rotatably supports the variable ring. And characterized in that:

In this gas turbine, even at a low load or the like, the mounting angle of each of the stator blades constituting one stator blade row can be maintained substantially constant, so that the occurrence of surging at a low load or the like and the occurrence of a It is possible to prevent damage to the wing. Therefore,
This gas turbine can exhibit stable performance even at low load and has high reliability

[0020]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of an axial compressor and a gas turbine according to the present invention will be described below in detail with reference to the drawings.

FIG. 1 is a partial sectional view showing a gas turbine according to the present invention. The gas turbine GT shown in the figure is applicable to various industries, and is suitable when used alone for power generation or when combined with a steam turbine to form a combined cycle plant. As shown in the figure, the gas turbine GT is composed of an axial-flow type compressor AC, a combustor CB, and an axial-flow type turbine AT, and is formed of a ferrite-based or martensitic-based compressor. A casing 2 including a casing 3 and a turbine casing 4
Having. The casing 5 accommodates the rotor 5 in which the compressor rotor 6 and the turbine rotor 7 are integrated by bolting. The rotor 5 includes a journal bearing 8 and a thrust bearing 9 provided on the compressor AC side, and a turbine A
It is supported by a journal bearing 10 provided on the T side, and is connected to a generator or the like on the compressor AC side.

In this gas turbine GT, each of the bearings 8 and 9 on the compressor AC side is supported by the compressor casing 3 by a plurality of radial struts 11. Supported by Further, the bearing 10 on the turbine AT side is supported on the turbine casing 4 by a plurality of tangential struts 14, and the turbine casing 4 is supported at the installation location by a trunnion support 15. Thus, the thermal expansion and contraction of the casing 2, the rotor 5, and the like are absorbed on the turbine AT side, so that the thermal effect on the connection between the rotor 5 and the generator EG1 can be reduced.

As shown in FIG. 1, the compressor rotor 6 has a plurality of stages (in this case, 17 stages) of compressor bucket rows CRC. Specifically, the compressor rotor 6 has a plurality of compressor disks 16 on which a number of compressor rotor blades CR constituting a cascade are implanted. Are combined. Further, inside the compressor casing 3, each compressor rotor cascade CRC of the compressor rotor 6 is provided.
And a plurality of stages (in this case, 17 stages) of compressor stationary blade rows CSC are arranged. Each compressor stationary cascade CS
C is configured by attaching a large number of compressor stationary blades CS arranged concentrically to the compressor casing 3.

The compressor stationary blade row C located at the first stage
In front of the SC, an inlet guide cascade IGVC is provided. In this compressor AC, by operating the IGV deflection mechanism 18, the mounting angle of each inlet guide vane IGV can be set freely. Thereby, the starting characteristics of the gas turbine GT can be optimized.

The compressor AC having the above-described configuration is configured such that each of the moving blade rows CRC of the compressor rotor 6 and the respective stationary blades fixed to the compressor casing 3 are driven to rotate the air sucked through the suction port 19. The pressure is increased with the row CSC and supplied to the combustor CB. The combustor CB is a cannula type combustor having a plurality of (for example, 16 to 20) combustor inner cylinders 20, and mixes fuel such as natural gas into pressurized air to burn. A part of the combustion air combusted in the combustor CB is bypassed by a bypass valve 22 attached to each combustor transition piece 21, and is guided to the turbine AT in a state where the air-fuel ratio in the combustion zone is optimally controlled. .

The turbine AT has an annular flow path 30 connected to the combustor transition piece 21, and combustion air flowing through the annular flow path 30 is provided in a plurality of stages (in this case,
4 stages), a turbine stator cascade TSC disposed over
It is expanded by the turbine rotor cascade TRC attached to the turbine rotor 7 over a plurality of stages (in this case, four stages). As a result, the energy of the combustion air is changed to a rotational torque, and the generator and the like are driven.

The turbine rotor 7 has a turbine rotor cascade TR
C has a plurality of turbine disks 31 having a large number of turbine blades TR implanted therein. Each turbine disk 31 is fixed to a turbine shaft 32. The turbine vane row TSC is configured by fixing a large number of turbine vanes TS arranged concentrically to the turbine casing 4.

FIG. 2 is a partial cross-sectional view showing a main part of a compressor AC constituting the gas turbine GT. As described above, the mounting angle of each of the inlet guide vanes IGV of the compressor AC can be freely set by operating the IGV changing mechanism 18, but in this compressor AC, in addition to this, The first to fifth stages of the compressor stationary blades CS1 to CS5
Can be freely set. This makes it possible to further optimize the startup characteristics of the gas turbine GT. Here, the deflection mechanism 41 of each of the compressor stationary blades CS constituting the first stage has the same configuration as the IGV deflection mechanism 18. Therefore, the description is omitted here, and each of the stationary blades CS2, CS3, CS4, CS5 constituting the second to fifth stages is omitted.
The bending mechanisms 42, 43, 44, and 45 will be described in detail.

Each of the deflection mechanisms 42 to 45 includes a variable ring 42R, 43R, 44R, 45R formed of a ferrite or martensite material. Each of the variable rings 42R to 45R has a horizontal two-part structure, covers the outer periphery of the compressor casing 3, and
It is arranged so as to correspond to each of the compressor rotor cascades CSC of the stages from the fifth stage to the fifth stage. Each variable ring 42R to 45R is individually
Alternatively, it is rotationally driven around the main shaft 17 by an integral variable ring drive actuator. In the case where an integrated variable ring drive actuator is employed, the rotation amounts of the variable rings 42R to 45R are slightly different from each other.
Variable rings 42R to 45R via a predetermined link mechanism or the like
And the variable ring drive actuator. These variable rings 42R to 45R are respectively associated with the corresponding compressor stationary blades CS2, CS3, CS4.
Works with CS5.

More specifically, taking the deflection mechanism 42 as an example, an arm 42A extending toward the downstream side in the flow direction of the handled fluid is provided on the stationary blade shaft 42S of each stationary blade CS2 penetrating through the compressor casing 3. Attached, each arm 42
The leading end of L is connected to one end of the link 42L via a connecting pin. The other end of each link 42L is connected to a variable ring 42R via a connecting pin. Similarly, the other variable rings 43 to 45 are also connected to the stationary blade shafts 43S to 43C of the compressor stationary blades CS3 to CS5 via the links 43L to 45L and the arms 43A to 45A, respectively.
45.

Each variable ring 42 of each of the deflection mechanisms 42 to 45
Each of R to 45R is rotatably supported by a support ring 50 arranged so as to cover the outer peripheral surface of the compressor casing 3. That is, each of the variable rings 42R-45
R has rollers 46 rotatable around an axis parallel to the main shaft 17 as shown in FIG. 3, and each of the rollers 46 rolls on a rail formed on the inner peripheral surface of the support ring 50. It is free. The support ring 50 is made of an austenitic material (high thermal expansion material) such as 18-8 stainless steel, and has a horizontal two-part structure as shown in FIG. The support ring 50 has guide blocks 51 at at least three places (four places in the present embodiment) on the circumference, and a hole extending in the radial direction of the main shaft 17 is formed inside each guide block 51. ing.

On the other hand, on the outer peripheral surface of the compressor casing 3,
A rod-shaped guide pin 52 extending in the radial direction of the main shaft 17
(Guide members) are at least three places (in the present embodiment, four guide members)
). Each guide pin 52 is slidably inserted into a hole formed in each guide block 51 of the support ring 50. Thereby, the support ring 50 is
The compressor is supported so as to be expandable and contractible (heat expandable and contractible) with respect to the compressor casing 3. In the compressor AC of the gas turbine GT, since the guide pins 52 as guide members are provided at at least three places on the outer periphery of the compressor casing 3, the support ring 50 that expands and contracts is connected to the compressor casing 3 (the main shaft 17). Can be reliably maintained concentric with respect to.

The guide pins 52 are preferably rotatable by being mounted on the compressor casing 3 via bearings 53, as shown in FIGS. Further, while fixing the guide pin 52 to the support ring 50 side,
It may be configured to be slidable with respect to the compressor casing 3. Further, a key may be used instead of the rod-shaped guide pin 52.

Next, the operation of the compressor AC constituting the gas turbine GT will be described.

When the gas turbine GT (compressor AC) is started, the temperature of the fluid (air) inside the compressor casing 3 rises, especially toward the rear stage.
Therefore, the temperature of the compressor casing 3 itself also increases due to the increase in the temperature of the handled fluid, and the compressor casing 3 thermally expands. On the other hand, since the variable rings 42R to 45R connected to the compressor stationary blades CS2 to CS5 are provided on the outer periphery of the compressor casing 3, the influence of the temperature rise of the handled fluid is reduced. The degree of expansion is smaller than that of the compressor casing 3.

On the other hand, the compressor AC of this gas turbine GT
Then, the support ring 5 supporting each of the variable rings 42R to 45R
0 is disposed so as to cover the outer periphery of the compressor casing 3,
Further, it is supported by the compressor casing 3 so as to be expandable and contractible in the radial direction of the main shaft 17. That is, the compressor AC
Then, in addition to the variable rings 42R to 45R, the support ring 5
0 is also disposed away from the compressor casing 3. Therefore, for example, during operation of the gas turbine GT (compressor AC), the temperature of each of the variable rings 42R to 45R and the temperature of the support ring 50 are maintained lower than the casing temperature, and the temperature difference between the two is reduced. It becomes possible.

As a result, the difference in the amount of thermal expansion and contraction between each of the variable rings 42R-45R and the support ring 50 can be reduced, so that each of the variable rings 42R during operation of the gas turbine GT (compressor AC). 45R expands and contracts with respect to the compressor casing 3 (main shaft 17) to the same degree as the support ring 50. This makes it possible to reduce the play between the variable rings 42R to 45R when the variable rings 42R to 45R are supported by the support ring 50, regardless of the thermal expansion of the compressor casing 3.
Can always be kept concentric with the main shaft 17 (compressor casing 3). Therefore, the compressor A of the gas turbine GT
In C, the mounting angle of each of the compressor stationary blades CS2 to CS5 constituting each of the stator blade rows CSC can be maintained substantially constant even at a low load or the like. Damage to the blades CS and the compressor blades CR can be prevented. .

Further, in the compressor AC of the gas turbine GT, the support ring 50 includes the compressor casing 3 and the respective variable rings 4.
It is formed of an austenitic material having a higher thermal expansion coefficient than the material forming 2R to 45R. As described above, by forming the support ring 50 from the high thermal expansion material, each of the variable rings 42R to 45R
Even closer to the compressor casing 3 than in FIG.
), The difference in the amount of thermal expansion between each of the variable rings 42R to 45R and the support ring 50 can be similarly maintained regardless of the casing temperature. This makes it possible to minimize the backlash between the variable rings 42R to 45R when supporting the variable rings 42R to 45R on the support ring 50, regardless of the degree of thermal expansion of the compressor casing 3.
To 45R can always be maintained concentric with the main shaft 17 (compressor casing 3).

FIGS. 4 and 5 are enlarged partial cross-sectional views of another embodiment of the axial compressor according to the present invention. FIG.
In the compressor AC shown in (1), the stationary blade row CSC of the latter side stationary row (the fifth stage in the present embodiment) under severe temperature conditions
In contrast, the temperature of the variable ring 47 and the compressor casing 3
Ring temperature adjusting means for reducing the difference from the temperature of the ring. In the deflection mechanism 45X shown in FIG. 4, a heating medium flow path P formed in the variable ring 47, and a heating medium supply pipe 48 for guiding a handled fluid from the annular flow path in the compressor casing 3 to the heating medium flow path P Constitutes a ring temperature adjusting means.

As shown in FIG. 5, the heat medium flow path P is formed inside the variable ring 47 so as to have a C-shape. A heat medium inlet 49a is provided at one end (lower end in the figure) of the heat medium flow path P, and a heat medium outlet 49b is provided at the other end (upper end in the figure). Is provided. One end of the heat medium supply pipe 48 is connected to the heat medium extraction plug 33 attached to the compressor casing 3,
The other end is connected to the heat medium inlet 49a of the variable ring 47.

Under such a configuration, during operation of the gas turbine GT (compressor AC), a part of the fluid (air) handled from the inside of the compressor casing 3 is supplied to the heat medium extraction plug 33.
And is supplied to a heat medium flow path P formed in the variable ring 47 via a heat medium supply pipe 48. Thereby, the temperature of the variable ring 47 and the temperature of the compressor casing 3 are similarly maintained, and the difference in the amount of thermal expansion between the two can be reduced. Therefore, the play between the variable ring 47 and the compressor casing 3 can be minimized, and the variable ring 47 is always connected to the compressor casing 3 (main shaft).
And can be kept concentric.

In this case, since the support ring (not shown) can expand and contract in the radial direction of the main shaft 17 with respect to the compressor casing 3, the support ring is expanded and contracted so as to be concentric with the main shaft 17 (compressor casing 3). The variable ring 47 follows. Further, the handled fluid supplied to the heat medium flow path P of the variable ring 47 flows through the heat medium flow path P and then is discharged from the heat medium outlet 49b to the outside of the system. Is extremely small and has no practical problem.

FIG. 6 is an enlarged partial cross-sectional view of a main part showing still another embodiment of the axial compressor according to the present invention. Also in the compressor AC shown in the figure, the stationary blade row CS of the latter stationary blade row (the fifth stage in the present embodiment) where the temperature condition is severe is also used.
For C, a ring temperature adjusting means for reducing the difference between the temperature of the variable ring 45R and the temperature of the compressor casing 3 is provided. In the deflection mechanism 45Y shown in FIG. 6, an annular pipe 55 provided around the variable ring 45R and having a plurality of outlets 55a, and a heat medium that guides a fluid to be handled from the annular flow path in the compressor casing 3 to the annular pipe 55 are provided. Ring temperature adjusting means is constituted by the supply pipe 56. In the annular pipe 55, each outlet 55a faces the surface of the variable ring 45R, and
It is arranged so as to cover the outer periphery of the variable ring 45R. Further, one end of the heat medium supply pipe 56 is connected to a heat medium extraction plug 33 attached to the compressor casing 3,
The other end is connected to the annular pipe 55.

Under such a configuration, during operation of the gas turbine GT (compressor AC), a part of the fluid (air) handled from the inside of the compressor casing 3 is subjected to the heat medium extraction plug 33.
Is extracted via the heating medium supply pipe 56 and the annular pipe 55
Supplied to Then, the handled fluid supplied to the annular pipe 55 is blown from the outlets 55a to the surface of the variable ring 45R. Thereby, the temperature of the variable ring 45R and the temperature of the compressor casing 3 are similarly maintained, and the difference in the amount of thermal expansion between the two can be reduced. Therefore, play between the variable ring 45R and the compressor casing 3 can be minimized, and the variable ring 45R can always be maintained concentric with the compressor casing 3 (main shaft).

Also in this case, since the support ring (not shown) can expand and contract in the radial direction of the main shaft 17 with respect to the compressor casing 3, the expansion ring is concentric with the main shaft 17 (compressor casing 3). Follow the variable ring 45R to shrink. Further, the loss of the compressor AC caused by extracting a part of the fluid (air) from the inside of the compressor casing 3 is extremely small, and there is no practical problem.

Although the above-described axial flow compressor AC has been described as constituting the gas turbine GT, it is not limited to this. That is, the axial flow compressor according to the present invention can be configured as a single compressor applied to blast furnace blowing, air source compression of an air liquefaction apparatus, and the like.

[0047]

The axial compressor and the gas turbine according to the present invention are configured as described above, so that the following effects are obtained. That is, it is possible to rotate around the main shaft of the compressor, and the variable ring associated with each vane is rotatable on a support ring attached to the compressor casing so as to be expandable and contractible in the radial direction of the main shaft. , The mounting angle of each vane constituting one vane row can be kept constant irrespective of the thermal expansion of the compressor casing, and stable performance can be exhibited even at low load. Yes, and highly reliable axial compressor, and
A gas turbine can be realized.

[Brief description of the drawings]

FIG. 1 is a partial sectional view showing a gas turbine according to the present invention.

FIG. 2 is an enlarged partial cross-sectional view of a main part of a compressor included in the gas turbine shown in FIG.

FIG. 3 is a cross-sectional view showing a support ring attached to a compressor casing.

FIG. 4 is an enlarged partial sectional view of a main part showing another embodiment of the axial compressor according to the present invention.

5 is a sectional view of a variable ring provided in the axial compressor shown in FIG.

FIG. 6 is an enlarged partial sectional view showing still another embodiment of the axial compressor according to the present invention.

[Explanation of symbols]

GT: gas turbine, AC: compressor, AT: turbine
CB: Combustor, 2: Cabin, 3: Compressor casing, 4 ...
Turbine casing, 5 ... rotor, 6 ... compressor rotor,
7 ... turbine rotor, 8,10 ... journal bearing, 9 ...
Thrust bearing, 11 ... radial strut, 12 ... rigid support, 14 ... tangential strut, 1
5 ... trunnion support, 16 ... compressor disk, 17
... Main shaft, 20... Combustor inner cylinder, 21.
Bypass valve, 30: annular flow path, 31: turbine disk, 32: turbine shaft, 33: heat medium extraction plug, 42,
43, 44, 45, 45X, 45Y...
R, 43R, 44R, 45R, 47 ... variable ring, 42
A, 43A, 44A, 45A ... arm, 42L, 43
L, 44L, 45L link, 42S, 43S, 44
S, 45S: stationary blade axis, 46: roller, 48, 56: heat medium supply pipe, 50: support ring, 51: guide block, 52:
Guide pin, 55: annular pipe, 55a: outlet, CR1,
CR2, CR3, CR4, CR5 ... Compressor blade, CRC
... Compressor bucket row, CS1, CS2, CS3, CS4, C
S5: compressor stationary blade, TR: turbine blade, TRC: turbine blade row, TS: turbine blade, TSC: turbine blade row.

 ────────────────────────────────────────────────── ─── Continuing on the front page (72) Inventor Taku Ichiyanagi 2-9-19-1 Shinhama, Arai-machi, Takasago-shi, Hyogo F-term in Takaishi Engineering Co., Ltd. 3H034 AA02 AA16 BB03 BB08 BB17 CC03 DD07 EE02

Claims (7)

[Claims] An axial flow compressor having a stationary blade row provided in a casing and a moving blade row attached to a main shaft, wherein an installation angle of each of the stationary blades constituting the stationary blade row can be changed. A variable ring that is linked to each of the stationary blades and that can rotate around the main shaft; and a variable ring supported by the casing so as to be expandable and contractible in a radial direction of the main shaft. And a support ring for rotatably supporting the compressor. 2. A guide member extending in a radial direction of the main shaft, fixed to one of the support ring and the casing, and slidable with respect to the other, is provided at at least three places. The axial compressor according to claim 1, wherein: 3. The axial compressor according to claim 1, wherein the support ring is formed of a high thermal expansion material. 4. The axial flow compressor according to claim 1, further comprising a ring temperature adjusting means for reducing a difference between a temperature of the variable ring and a temperature of the casing. 5. The ring temperature adjusting means includes a heat medium flow path formed in the variable ring, and a heat medium supply pipe for guiding a fluid to be handled from the annular flow path in the casing to the heat medium flow path. The axial compressor according to claim 4, characterized in that: 6. The ring temperature adjusting means is provided around the variable ring and has an annular pipe having a plurality of outlets, and a heat medium supply for guiding a fluid to be handled from the annular flow path in the casing to the annular pipe. The axial compressor according to claim 4, comprising a tube. 7. A gas turbine in which a working fluid is pressurized by a compressor and burned in a combustor, and the temperature-pressurized working fluid is expanded by a turbine to generate power, wherein the compressor is provided in a compressor casing. It has a stationary blade row provided, and a moving blade row attached to the main shaft, it is possible to change the mounting angle of each of the stationary blades constituting the stator blade row, in cooperation with each of the stationary blades A variable ring that can be rotated around the main shaft; and a support ring that is supported by the casing so as to be able to expand and contract in the radial direction of the main shaft and rotatably supports the variable ring. A gas turbine characterized by the above.