Methods and apparatus for adjusting gas turbine engine variable vanes

• US 6,471,471 B1
• Filed: 04/04/2001
• Issued: 10/29/2002
• Est. Priority Date: 04/04/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bouyer, Mark Jeffery
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Edgar, Richard A.
• Application Number:
  US09/826,107
• Publication Number:
  US 20020146316A1
• Time in Patent Office: 573 Days
• Field of Search: 415/159, 415/160, 415/191, 415/208.2, 415/199.5, 415/1
• US Class Current: 415/160
• CPC Class Codes: F01D 17/16 by means of nozzle vanes
• 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

Abstract

A gas turbine engine including a variable geometry system that includes a mounting system to facilitate extending a useful life of a variable geometry system is described. The engine includes a high pressure compressor including a plurality of variable vanes and rotating vanes. The variable geometry system is coupled to an actuator and includes a master lever, an aft mount, and a slot and groove joint. The master lever is coupled to the aft mount with the slot and groove joint, and adjusts a position of the variable vanes without inducing angular displacement on the aft mount.

Claims

1. A method for assembling a variable geometry system for a gas turbine engine including a high pressure compressor, the variable geometry system including a master lever and at least one aft mount, the high pressure compressor including a plurality of variable vanes, said method comprising the steps of:

coupling the master lever to the aft mount using a slot and groove joint, to adjust the position of the high pressure compressor variable vanes during activation of the variable geometry system; and

securing the aft mount to the gas turbine engine with a mounting lug that prevents angular displacement of the aft mount during activation of the variable geometry system.

2. A method in accordance with claim 1 wherein said step of coupling the master lever to the aft mount further comprises the step of coupling the master lever to the slot and groove joint with a sleeve bearing.

3. A method in accordance with claim 1 wherein said step of coupling the master lever to the aft mount further comprises the step of coupling the master lever to the slot and groove joint with a spherical bearing.

4. A method in accordance with claim 1 wherein said step of coupling the master lever to the aft mount further comprises the step of using a slot and groove joint having at least one of a dovetail-shaped groove and a substantially cylindrical-shaped groove.

5. A variable geometry system for a gas turbine engine, said variable geometry system comprising:

a master lever; and

an aft mount, said master lever coupled to said aft mount with a slot and groove joint, and configured to adjust a position of variable vanes during activation of said variable geometry system, said aft mount comprising at least one mounting lug securing said aft mount to the gas turbine engine, said mounting lug configured to prevent angular displacement of said aft mount during activation of said variable geometry system.

6. A variable geometry system in accordance with claim 5 wherein said master lever coupled to said slot and groove joint with a spherical bearing.

7. A variable geometry system in accordance with claim 5 wherein said master lever coupled to said slot and groove joint with a sleeve bearing.

8. A variable geometry system in accordance with claim 5 wherein said slot and groove joint configured to restrict movement of said master lever to two-dimensional planar motion.

9. A variable geometry system in accordance with claim 5 wherein said slot and groove joint is coated with a wear resistant material.

10. A variable geometry system in accordance with claim 5 wherein said slot and groove joint comprises a substantially cylindrical-shaped groove.

11. A variable geometry system in accordance with claim 5 wherein said slot and groove joint comprises a dovetail-shaped groove.

12. A gas turbine engine comprising:

a high pressure compressor comprising a plurality of variable vanes; and

a variable geometry system configured to re-direct airflow through said high pressure compressor, said variable geometry system comprising a master lever and an aft mount, said master lever coupled to said aft mount and configured to adjust a position of variable vanes during activation of said variable geometry system, said aft mount coupled to said master lever with a slot and groove joint.

13. A gas turbine engine in accordance with claim 12 wherein said variable geometry system further comprises at least one mounting lug securing said aft mount to said gas turbine engine, said mounting lug configured to prevent angular displacement of said aft mount during activation of said variable geometry system.

14. A gas turbine engine in accordance with claim 12 wherein said variable geometry system master lever coupled to said slot and groove joint with at least one of a spherical bearing and a sleeve bearing.

15. A gas turbine engine in accordance with claim 12 wherein said variable geometry system slot and groove joint configured to restrict movement of said master lever to two-dimensional planar motion.

16. A gas turbine engine in accordance with claim 12 wherein said variable geometry slot and groove joint comprises a dovetail-shaped groove.

17. A gas turbine engine in accordance with claim 12 wherein said variable geometry slot and groove joint comprises a substantially cylindrical-shaped groove.

18. A gas turbine engine in accordance with claim 12 wherein the slot and groove joint is coated with a wear resistant material.