JP3482093B2 - Gas turbine compressor stationary blade variable device - Google Patents

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a variable vane device of a gas turbine compressor using an axial air compressor. 2. Description of the Related Art A variable compressor / static vane type gas turbine having an axial fixed point in the center of a vehicle compartment will be described with reference to FIG. As shown in FIG. 3, the rotor of the compressor stationary vane variable gas turbine is constructed by connecting an axial compressor rotor 1 and a turbine rotor 2 to one shaft and supported by a pair of bearings 3. I have. The air compressed by the compressor rotor 1 is taken out from the outside passage of the double pipe 4, and the combustion gas flows in through the inside passage to drive the turbine rotor 2. [0004] This type of gas turbine is called an external combustion type gas turbine, and is a pressurized fluidized bed combustor (PFBC).
erized Fluidized Bed Combustor) plant and blast furnace gas-fired gas turbine. The casing 5 is axially fixed at a central portion having the double pipe 4, and the thermal expansion in the axial direction indicated by an arrow is provided by a flexible plate support 6 on the compressor side and by a trunnion support 7 on the turbine side. Each is absorbed. The support plate 9 supporting the fixed key 8 at the center of the vehicle compartment has flexibility in the radial direction. An inlet guide vane 10 and a front stage stationary vane 11 of a compressor.
In order to improve the efficiency at the time of partial load, widen the surging limit, and facilitate the start of the gas turbine, a variable pitch mechanism is employed. [0007] The conventional stator vane variable device of the compressor vane variable gas turbine comprises an actuator 12 having a rod 13, a link mechanism 14, a vane variable ring 15, and an arm 16, and is mounted on a foundation. The rod 13 of the installed actuator 12 moves the stator blade variable ring 15 in the axial direction via the link mechanism 14, and the arm 16 drives the inlet guide blade 10 and the blade shaft 17 of the preceding stage stator blade 11 to rotate. . The axial movement of the variable stator vane ring 15 is as follows.
It has been guided by the variable ring 15, a rod receiver 18 attached to the cabin 5, and a guide rod 19 supported by the rod receiver 18. In a conventional variable vane device of a gas turbine compressor, a simple link mechanism is attached to an actuator having a variable vane ring attached to a vehicle cabin fixed on a foundation. When the vehicle compartment moves in the axial direction due to thermal expansion, the relative position between the variable stator vane ring and the actuator rod changes, and the vane angle changes regardless of the actuator. For this reason, the thermal efficiency of the gas turbine may be reduced, or the compressor may generate surging. The present invention seeks to solve the above problems. According to a first aspect of the present invention, there is provided a variable vane device for a gas turbine compressor according to the first aspect of the present invention. A first arm having one end pin-connected to a tip end of an axially extendable rod of an actuator disposed on a base, and a base having one end mounted on the base. Is connected to a second arm, and an L-shaped first lever is connected to the other end of the second arm by a pin at the center of its rotational axis and is connected to the other end of the first arm by a pin. An L-shape in which the other end of the first lever and the center of rotation are connected to one end and the center of rotation via a first and a second rod, respectively, and the other end is connected to the variable stator vane ring with a pin. The second lever, the center of rotation of the second lever A third arm is provided, one end of which is pin-connected, and the other end of which is pin-connected to the vehicle compartment. In the above, when the portion of the vehicle interior where the stationary blade variable ring is provided moves in the axial direction due to thermal expansion, the stationary blade variable ring moves at the same time, and the second lever and the third arm also move. I do. In this case, a force is applied to the other end and the rotation center of the first lever from the one end of the second lever and the rotation center via the first and second rods. While descending while maintaining the posture, the first and second arms are simultaneously inclined, so that no force is applied to the rod of the actuator and its position does not change. for that reason,
The thermal expansion of the passenger compartment may have no effect on the operation of the actuator. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A variable vane device for a gas turbine compressor according to one embodiment of the present invention will be described with reference to FIG. The present embodiment relates to a device for rotationally driving the blade guide 17 of the inlet guide vane 10 and the front-stage vane 11 via the vane variable ring 15 and the arm 16.
The other parts are the same as those of the conventional apparatus, and thus detailed description thereof is omitted. In the variable vane device according to the present embodiment shown in FIG. 1, one end of a rod 13 that extends and contracts in the axial direction of the gas turbine of an actuator 12 disposed on a foundation is connected via a pin 28 to one end thereof. Arm 27, one end of which is pin-coupled to a support base 29 on the base, the other end of the arm 23 having its center of rotation connected and the other end of the arm 27 having one end pin-connected. An L-shaped lever 26, a rod 24 having one end pin-connected to the other end of the lever 26, a rod 25 having one end pin-connected to the other end of the arm 23 and the rotation center of the lever 26, An L-shaped lever 21 having one end and a rotation center respectively pin-connected to the other end of the lever 25 and the other end pin-connected to the stationary blade variable ring 15, and a rotation center of the lever 21 and the rod 25 One end of the other end is pin-connected is provided with an arm 22 which is pinned to the casing 5 at the other end. In the above description, when trying to rotationally drive the blade shaft 17 of the inlet guide vane 10 and the front stage stationary vane 11, the rod 13 of the actuator 12 is expanded and contracted. When the rod 13 expands and contracts, a force is applied to one end of the lever 26 via the arm 27, so that a rotational force about the rotation center is applied to the lever 26. This rotational force is transmitted to the lever 21 via the rods 24 and 25, and a rotational force is applied to the lever 21 with its rotation center as a fulcrum, so that the variable vane ring 15 is moved in the axial direction of the gas turbine. As a result, the inlet guide vane 10 and the preceding stage stationary vane 11 can be rotated. Next, the case where the stationary vane variable ring 15 moves in the axial direction due to the thermal expansion of the vehicle compartment 5 starting from the fixed key 8 will be described with reference to FIG. In the drawing, a solid line indicates a cold state and a dotted line indicates a thermal expansion. When the variable stator vane ring 15 moves in the axial direction by Δl due to thermal expansion, the lever 21 and the arm 22 move in the axial direction to the position indicated by the dotted line. At this time, since a downward force is applied to the lever 26 via the rods 24 and 25,
The arm 23 is inclined with the base as a fulcrum, and the rods 24, 2
5 is in the state shown by the dotted line, and the lever 26 is lowered to the position shown by the dotted line. However, the rod 13 of the actuator 12 disposed on the base has an inclined arm 27 whose one end is pin-coupled to its tip, so that its position does not change, and thermal expansion does not affect the actuator at all. . As a result, the angle of the variable stator vane does not change due to thermal expansion, and it is possible to prevent the efficiency of the gas turbine axial flow compressor from lowering due to thermal expansion and prevent the occurrence of surging. The gas turbine compressor vane variable device according to the present invention is provided with a vane variable ring movable in the axial direction outside a portion where the axial movement is caused by the thermal expansion of the vehicle compartment. In a gas turbine, an end of a rod that extends and contracts in the axial direction of an actuator disposed on a foundation is pin-connected at one end via a first arm, and the rotation center is connected via a pin to the foundation via a second arm. A shaped L-shaped first lever;
The other end of the first lever and the center of rotation are respectively pin-connected to the one end and the center of rotation via first and second rods via the first and second rods, and the other end is pin-connected to the variable stator vane ring and the center of rotation is the third center.
When the vehicle compartment thermally expands by providing the second lever pin-connected to the vehicle compartment via the arm of the first arm, the first lever is moved when the second lever and the third arm move in the axial direction. And the second
Arm tilts and the first lever descends, and has no effect on the rod of the actuator. Therefore, the angle of the variable vane does not change due to thermal expansion, and the axial flow for the gas turbine due to the thermal expansion of the vehicle compartment It is possible to prevent the efficiency of the compressor from lowering and the occurrence of surging.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a side view of a gas turbine compressor vane variable device according to an embodiment of the present invention. FIG. 2 is an operation explanatory view according to the embodiment. FIG. 3 is an explanatory view of a conventional device. [Description of Signs] 5 Chamber 8 Chamber center fixed key 10 Entrance guide vane 11 Front stage stationary vane 12 Actuator 13 Rod 15 Static vane variable ring 16 Arm 17 Blade shaft 21 Lever 22, 23 Arm 24, 25 Rod 26 Lever 27 Arm 28 Pin 29 Support base

──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor Kenichi Arase 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. (56) References JP-A-5-125960 (JP, A) JP-A-7-317501 (JP, A) JP-A-3-86001 (JP, U) (58) Fields investigated (Int. Cl. ⁷ , DB name) F02C 7 / 04-7/057 F02C 9/54 F04D 27 / 02,29 / 56

Claims (1)

(57) [Claim 1] In a gas turbine provided with a variable vane ring that is movable in the axial direction outside a portion where axial movement is caused by thermal expansion of the vehicle compartment, A first arm having one end pin-connected to the tip of the axially extendable rod of the actuator provided, a second arm having one end pin-connected to a base, and the other end of the second arm An L-shaped first lever whose center of rotation is pin-connected to the other end of the first arm and one end of which is pin-connected to the other end of the first arm; An L-shaped second lever whose center is connected to the pin via the first and second rods, and the other end of which is pin-connected to the variable stator vane ring, one end of which is connected to the rotation center of the second lever. A third arm coupled and the other end pinned to the passenger compartment; Gas turbine compressor stator blades variable and wherein the a.