Systems and Methods for Positioning Fairing Sheaths of Gas Turbine Engines

• US 20090243176A1
• Filed: 03/31/2008
• Published: 10/01/2009
• Est. Priority Date: 03/31/2008
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Alexander, Phillip
• Granted Patent: US 8,393,062 B2
• Time in Patent Office: Days
• US Class Current: 269/21
• CPC Class Codes: B25B 11/007 portable, e.g. handheld
• CPC Class Codes: B25B 5/14 Clamps for work of special profile using chains or strips B25B1/205
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: Y10T 29/12 Buckle making
• CPC Class Codes: Y10T 29/33 Stereotype-plate finishing
• CPC Class Codes: Y10T 29/49346 Rocket or jet device making
• CPC Class Codes: Y10T 29/5162 Lever operated

Abstract

Systems and methods for positioning fairing sheaths are provided. In this regard, a representative method includes using vacuum pressure to assist in moving opposing portions of a fairing sheath away from each other.

Claims

1. A system for positioning a fairing sheath of a gas turbine engine comprising:

a tool having a clamp and opposing gripping members;

the clamp being operative to clamp about a leading edge portion of a fairing sheath;

the gripping members being operative to pivot about the clamp, a first of the gripping members having a first contact face and a first seal positioned on the first contact face, a second of the gripping members having a second contact face and a second seal positioned on the second contact face, the first contact face opposing the second contact face, the first contact face and the first seal being operative to form a first vacuum chamber, the second contact face and the second seal being operative to form a second vacuum chamber.

2. The system of claim 1, wherein:

the clamp has a first clamp member and a second clamp member; and

the first clamp member and the second clamp member define a channel sized and shaped to receive a leading edge portion of a fairing sheath therein.

3. The system of claim 2, wherein:

the first clamp member has a first clamping surface and a first locating surface, the first clamping surface being operative to contact a surface of a fairing sheath, the first locating surface being operative to contact a surface of the fairing sheath such that a longitudinal position of the first contact surface of the first gripping member is established; and

the second clamp member has a second clamping surface and a second locating surface, the second clamping surface being operative to contact a surface of a fairing sheath, the second locating surface being operative to contact a surface of the fairing sheath such that a longitudinal position of the second contact surface of the second gripping member is established.

4. The system of claim 3, wherein:

the first clamping surface is located between the first locating surface and the first contact surface; and

the second clamping surface is located between the second locating surface and the second contact surface.

5. The system of claim 1, further comprising a first handle extending from the first of the gripping members and a second handle extending from the second of the gripping members handles such that positioning of the handles positions the gripping members.

6. The system of claim 5, further comprising a stop operative to prevent movement of the first handle and the second handle beyond a limit position at which damage to the fairing sheath could occur.

7. The system of claim 6, wherein the stop comprises a first stop member positioned on the first handle and a second stop member positioned on the second handle, the first stop member and the second stop member being operative to contact each other at the limit position.

8. The system of claim 6, wherein, at the limit position, the first contact surface and the second contact surface define an included angle of between approximately 4 and approximately 10 degrees.

9. The system of claim 6, wherein, at the limit position, the first contact surface and the second contact surface define an included angle of between approximately 5 and approximately 7 degrees.

10. The system of claim 1, further comprising a vacuum pressure source pneumatically communicating with the first of the gripping members and a second of the gripping members such that vacuum pressure is applied to the first vacuum chamber and to the second vacuum chamber.

11. The system of claim 1, wherein the first seal extends along a major axis having a length corresponding to a length of the fairing sheath.

12. The system of claim 11, wherein the clamp extends along a major axis having a length corresponding to the length of the first seal.

13. The system of claim 1, wherein the gripping members pivot about respective axes oriented parallel to a leading edge of the fairing.

14. A method for positioning a fairing sheath of a gas turbine engine comprising:

using vacuum pressure to assist in moving opposing portions of a fairing sheath away from each other.

15. The method of claim 14, wherein using vacuum pressure comprises:

forming a first vacuum seal with a first portion of the fairing sheath;

forming a second vacuum seal with a second portion of the fairing sheath;

moving the first vacuum seal away from the second vacuum seal.

16. The method of claim 15, wherein moving the first vacuum seal away from the second vacuum seal comprises pivoting the first vacuum seal and the second vacuum seal.

17. The method of claim 15, further comprising restricting movement of a portion of the fairing sheath during the moving.

18. The method of claim 15, wherein restricting movement comprises clamping a leading edge portion of the fairing sheath during the moving.

19. The method of claim 14, wherein using vacuum pressure is performed for installing the fairing sheath in a gas turbine engine.

20. The method of claim 14, wherein using vacuum pressure is performed for removing the fairing sheath from a gas turbine engine.