Seal support structure

Patent metadata

Field	Value
Publication number	US-2016115804-A1
Application number	US-201514921503-A
Country	US
Kind code	A1
Filing date	Oct 23, 2015
Priority date	Oct 23, 2014
Publication date	Apr 28, 2016
Grant date	—

Abstract

The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

First claim

What is claimed is:

1 . A seal support structure for a gas turbine engine, the seal support structure comprising:
a seal support configured to retain a circumferential seal; and an engine support configured for mounting the seal support structure to a gas turbine engine mount, wherein the engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support.

2 . The seal support structure of claim 1 , wherein the seal support includes a runner and a shoulder configured to retain the circumferential seal.

3 . The seal support structure of claim 1 , wherein each channel is configured to receive a retaining element of the engine mount.

4 . The seal support structure of claim 1 , wherein each channel is an elongated slot oriented in a radial direction to provide radial motion for the seal support and engine support.

5 . The seal support structure of claim 1 , wherein radial movement of the seal support structure includes radial movement of the seal support structure relative to a static gas turbine engine mount, wherein radial movement includes movement to and away from a rotating component.

6 . The seal support structure of claim 1 , wherein circumferential retention of the seal support includes retaining, by the seal support structure, a circumferential seal relative to a rotating component of the gas turbine engine.

7 . The seal support structure of claim 1 , wherein the engine support is a full ring including a plurality of channels.

8 . The seal support structure of claim 1 , wherein at least one of the engine support and circumferential seal are segmented.

9 . The seal support structure of claim 1 , wherein each channel is configured to reduce vibration transmitted from the gas turbine engine to the circumferential seal.

10 . The seal support structure of claim 1 , wherein the seal support is configured to retain a circumferential seal having at least one beam and at least one shoe.

11 . A sealing system for a gas turbine engine, the sealing system comprising:
a circumferential seal; and a seal support structure, the seal support structure including
a seal support configured to retain a circumferential seal, and
an engine support configured for mounting the seal support structure to a gas turbine engine mount, wherein the engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support.

12 . The sealing system of claim 11 , wherein the seal support includes a runner and a shoulder configured to retain the circumferential seal.

13 . The sealing system of claim 11 , wherein each channel is configured to receive a retaining element of the engine mount.

14 . The sealing system of claim 11 , wherein each channel is an elongated slot oriented in a radial direction to provide radial motion for the seal support and engine support.

15 . The sealing system of claim 11 , wherein radial movement of the seal support structure includes radial movement of the seal support structure relative to a static gas turbine engine mount, wherein radial movement includes movement to and away from a rotating component.

16 . The sealing system of claim 11 , wherein circumferential retention of the seal support includes retaining, by the seal support structure, a circumferential seal relative to a rotating component of the gas turbine engine.

17 . The sealing system of claim 11 , wherein the engine support is a full ring including a plurality of channels.

18 . The sealing system of claim 11 , wherein at least one of the engine support and circumferential seal are segmented.

19 . The sealing system of claim 11 , wherein each channel is configured to reduce vibration transmitted from the gas turbine engine to the circumferential seal.

20 . The sealing system of claim 11 , wherein the seal support is configured to retain a circumferential seal having at least one beam and at least one shoe.

Assignees

• United Technologies Corp

Inventors

• Wilson Ross
• Mccaffrey Michael G
• Farris John R
• Hall Theodore W
• Korzendorfer John J
• Vinson Elizabeth F
• Jacques Jeffrey Michael
• Paul John E
• Stoner Alan W
• Otero Edwin

Classifications

• F01D9/04 Primary

  forming ring or sector · CPC title

• F01D11/025

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D11/12

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title