Stator vane actuator in gas turbine engine

• US 6,769,868 B2
• Filed: 07/31/2002
• Issued: 08/03/2004
• Est. Priority Date: 07/31/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Harrold, Michael Charles
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): White, Dwayne J.
• Application Number:
  US10/209,244
• Publication Number:
  US 20040022624A1
• Time in Patent Office: 734 Days
• Field of Search: 415/149.4, 415/150, 415/159, 415/162, 415/1, 298/892.1, 298/892.2
• US Class Current: 415/150
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2260/50 Kinematic linkage, i.e. transmission of position

Abstract

An actuator for adjustable stator vanes in a gas turbine engine. A torque tube is rotatable about its axis, and supports devises which connect to links. The links are connected to rings, and rotate the rings when the torque tube rotates, thereby adjusting stator vanes connected to the rings. A linear actuator, having a motion axis parallel to the torque tube, drives the torque tube, through a linear-rotary convertor. The invention occupies less space on the engine, and requires no adjustment of the linear-rotary convertor after installation.

Claims

1. In a gas turbine engine having an engine axis defined therein, and having multiple rows of variable stator vanes, each row actuated by a respective ring, and each ring actuated by a respective actuation link, an apparatus for actuating the links, comprising:

a) a torque tube having an axis parallel to the engine axis, and bearing a plurality of devises, each connected to a respective actuation link;

b) a linear actuator, having an axis parallel to the engine axis, which actuates the torque tube; and

c) a base, removable from the engine, which supports both the torque tube and the actuator.

2. Apparatus for adjusting stator vane angle in a gas turbine engine having an engine axis, comprising:

a) a rotatable torque tube having a tube axis parallel with the engine axis;

b) means for producing changes in stator vane angle in response to rotation of the torque tube;

c) a hydraulic actuator which moves a rod in linear motion, parallel to the tube axis; and

d) a convertor which converts the linear motion of the rod to rotary motion of the torque tube.

3. Apparatus according to claim 2, wherein the convertor comprises a bell crank.

4. Apparatus for adjusting stator vane angle in a gas turbine engine having an engine axis, comprising:

a) a rotatable torque tube having a tube axis parallel with the engine axis;

b) means for producing changes in stator vane angle in response to rotation of the torque tube;

c) a hydraulic actuator which moves a rod in linear motion, parallel to the tube axis; and

d) a convertor, comprising a cam and follower, which converts the linear motion of the rod to rotary motion of the torque tube.

5. Apparatus, comprising:

a) a torque tube, rotatable about an axis;

b) a linear hydraulic actuator, which moves a rod parallel to said axis;

c) a linkage connecting the rod to the torque tube, causing movement of the rod to rotate the torque tube; and

d) one or more linkages linked to the torque tube, each connecting to a respective ring which actuates stator vanes on a gas turbine engine.

6. Apparatus according to claim 5, wherein the linkage comprises

e) a bell crank having first and second arms,

i) the first arm connecting to the rod, and

ii) the second arm connecting to a link which rotates the torque tube when moved.

7. Apparatus mountable to a compressor casing of a gas turbine engine, for actuating adjustable stator vanes, comprising:

a) a torque tube;

b) devises on the torque tube, each for actuating a stage of stator vanes;

c) a hydraulic actuator;

d) a linkage system for connecting the actuator to the torque tube; and

e) a base supporting the torque tube, hydraulic actuator, and linkage system.

8. A method of installing an actuator for adjustable stator vanes in a gas turbine engine, comprising:

a) installing an actuator assembly which includes an actuator and a torque tube rotated by the actuator;

b) performing no adjustment of linkages between the actuator and the torque tube; and

c) connecting the torque tube to vane linkages which adjust the stator vanes.

9. A method of installing an actuator for adjustable stator vanes in a gas turbine engine, comprising:

a) installing an actuator assembly which includes an actuator and a torque tube rotated by the actuator;

b) performing no adjustment of linkages between the actuator and the torque tube;

c) connecting the torque tube to vane linkages which adjust the stator vanes, and

d) adjusting one or more vane linkages.

10. Apparatus for controlling adjustable stator vanes in a gas turbine engine, comprising:

a) a torque tube containing clevises which are connectable to linkages which adjust the stator vanes;

b) a single actuator; and

c) a linkage connecting the actuator to the torque tube, which requires no adjustment after the apparatus is connected to the engine.

11. Apparatus according to claim 10, wherein no adjustment is required of the linkage after connection of the apparatus to the engine because adjustment was performed prior to connection.

12. Apparatus according to claim 10, wherein adjustment to the linkage was performed prior to connecting the apparatus to the engine.

13. Apparatus according to claim 10, wherein an axis of rotation is defined in the engine, and the actuator comprises an actuation rod which moves parallel with the axis of rotation.

14. Apparatus according to claim 10, wherein the linkage of paragraph (c) is adjustable.

15. Apparatus according to claim 10, wherein, in normal operation, the actuator, by itself, controls stator vane angle.

16. Apparatus according to claim 10, wherein the linkages of paragraph (a) are non-adjustable.

17. A system, comprising:

a) an axial flow gas turbine (202) engine having an axis of rotation (45);

b) a linear actuator (200) having an axis of movement (205) which is parallel to the axis of rotation (45);

c) a torque tube (71) having a tube-axis (73) which is parallel to both the axis of rotation (45) and the axis of movement (205);

d) a plurality of devises (76) mounted to the torque tube (71);

e) a link (51) linking each clevis (76) to a respective ring (39) which rotates a set of stator vanes (24); and

f) means (210) for converting linear movement of the linear actuator (200) to rotary movement of the torque tube, to thereby rotate the rings.

18. System according to claim 17, wherein the means (210) comprises a bell crank (91).