Gas turbine engine seal

Patent metadata

Field	Value
Publication number	US-10731493-B2
Application number	US-201414783048-A
Country	US
Kind code	B2
Filing date	Apr 10, 2014
Priority date	Apr 12, 2013
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.

First claim

Having thus described the invention, what is claimed is:

1. A gas turbine engine stator assembly having an axis and a pair of radially offset first and second components, said first and said second components being sealed to each other by a seal comprising:
an axially resilient seal carrier fixed to said first component, said seal carrier being fixed to said first component at a radially outer portion of said seal carrier, said seal carrier extending from said first component toward said second component and terminating at a radially inner portion of said seal carrier proximal to said second component, said radially inner portion of said seal carrier comprising a pair of radially spaced radially resilient jaws adapted to receive a sealing element there between in clamped, compressive engagement with said jaws, said sealing element being in sealing contact with said second component, said seal carrier being axially resilient to accommodate differential axial expansion and contraction and differential axial movement of said first and said second components;
the pair of radially spaced radially resilient jaws comprising a first jaw and a second jaw, the first jaw configured with a first recess, and the second jaw configured with a second recess arranged opposite the first recess;
the sealing element comprising braided or plaited strands of material clamped between the first jaw and the second jaw; and
a first portion of the sealing element projecting in a first radial direction into the first recess, and a second portion of the sealing element projecting in a second radial direction into the second recess, wherein the second radial direction is radially opposite the first radial direction.

2. The gas turbine engine stator assembly of claim 1 wherein said seal carrier and said jaws are generally annular and said sealing element comprises a rope seal, and the rope seal is clamped and compressed between the first jaw and the second jaw.

3. The gas turbine engine stator assembly of claim 1 wherein said first and second components comprise an engine case and a turbine outer air seal.

4. The gas turbine engine stator assembly of claim 3 wherein said engine case is disposed radially outwardly of said turbine outer air seal, said seal carrier being fixed to said engine case at said radially outer portion of said seal carrier.

5. The gas turbine engine stator assembly of claim 4 wherein said radially outer portion of said seal is apertured to accommodate a fastener there through, said fastener fixing said seal carrier to said engine case.

6. The gas turbine engine stator assembly of claim 5 wherein said engine case includes a seal mounting flange, said seal carrier being fixed to said engine case at said seal mounting flange and wherein said fastener comprises a threaded fastener.

7. The gas turbine engine stator assembly of claim 1 wherein said carrier comprises a pair of mutually axially overlying resilient leaves, each of said leaves extending radially inwardly from said one component and terminating at a radially inner portion which includes one of said jaws formed integrally therewith.

8. The gas turbine engine stator assembly of claim 7 wherein said jaws are annular and circumferentially segmented to provide said radial resilience.

9. The gas turbine engine stator assembly of claim 1 , wherein
the second component is configured with a notch formed by a radially extending surface of the second component and an axially extending surface of the second component;
the sealing element projects axially out from the radially inner portion of the seal carrier into the notch;
the sealing element axially contacts the radially extending surface; and
the sealing element is radially outboard of and radially spaced away from the axially extending surface by a gap.

10. A rope seal for sealing a first component of a gas turbine engine having a central axis to a second component thereof, said rope seal comprising:
an axially resilient seal carrier adapted for mounting on said first component of said gas turbine engine at a radially outer portion of said seal carrier, said seal carrier extending radially inwardly from said first component;
said seal carrier being axially resilient to accommodate differential axial expansion and contraction and relative axial movement of said first and second components due to thermal and pressure conditions of a flow of working fluid through said gas turbine engine;
said seal carrier at a radially outer portion thereof, being fixed to said first component, said seal carrier including a radially inner portion, opposite said radially outer portion and provided with a pair of radially spaced, axially extending, radially resilient jaws; and the pair of radially spaced radially resilient jaws comprising a first jaw and a second jaw, the first jaw configured with a first recess, and the second jaw configured with a second arranged opposite the first recess;
a rope sealing element formed from a plurality of strands of material that are disposed between said radially resilient jaws in clamped engagement therewith; and a first portion of the rope sealing element projecting in a first radial direction into the first recess, and a second portion of the rope sealing element projecting in a second radial direction into the second recess, wherein the second radial direction is radially opposite the first radial direction
said seal carrier being adapted to locate said rope sealing element in preloaded sealing engagement with said second component of said gas turbine engine.

11. The rope seal of claim 10 wherein said seal carrier including said jaws is generally annular.

12. The rope seal of claim 10 wherein said seal carrier comprises a pair of axially overlying resilient leaves, each of said leaves extending radially inwardly from said radially outer portion of said seal carrier, each of said leaves having a radially inner portion which includes one of said jaws formed integrally therewith.

13. The rope seal of claim 10 wherein said jaws are circumferentially segmented to provide said radial resilience.

14. The rope seal of claim 10 , wherein said seal carrier is adapted for mounting on a case of the gas turbine engine.

15. The rope seal of claim 10 wherein said rope sealing element is adapted for sealing engagement with a turbine outer air seal of said gas turbine engine.

16. The rope seal of claim 10 wherein said rope sealing element is formed at least in part from refractory ceramic fibers.

17. The rope seal of claim 10 wherein said rope sealing element is formed at least in part from metallic wires.

18. The rope seal of claim 10 wherein said seal carrier is formed form a nickel-based superalloy.

Assignees

• United Technologies Corp
• Ratheyon Tech Corporation

Inventors

• Davis Timothy M
• Rogers Mark J
• Broomer Mark
• Mcgarrah Craig R
• Roy Thill Carson A

Classifications

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F01D9/04

  forming ring or sector · CPC title

• F05D2300/177

  Ni - Si alloys · CPC title

• F05D2300/175

  Superalloys · CPC title