Seals for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016290150-A1
Application number	US-201414394215-A
Country	US
Kind code	A1
Filing date	Apr 21, 2014
Priority date	Jun 21, 2013
Publication date	Oct 6, 2016
Grant date	—

Abstract

The present disclosure relates to a first seal for an aircraft blade outer air seal (“BOAS”) comprising a first portion comprising a first channel and a second channel, and a second portion comprising a first projection and a second projection, wherein the first projection slidably couples to the first channel and the second projection slidably couples to the second channel. The first portion and/or the second portion may be coated with a low friction substance. The first portion may be coupled to a vane support and/or a BOAS, and the second portion may be coupled to a first OAS support. The first seal may enable a radial translation of the BOAS in response to an aircraft maneuver.

First claim

1 . A first seal comprising:
a first portion comprising a first channel and a second channel; and a second portion comprising a first projection and a second projection,
wherein the first projection slidably couples to the first channel and the second projection slidably couples to the second channel.

2 . The first seal of claim 1 , wherein at least one of the first portion or the second portion is coated with a low friction substance.

3 . The first seal of claim 1 , wherein the first seal is situated such that the first seal accommodates a relative axial motion.

4 . The first seal of claim 1 , wherein the first portion is coupled to a blade outer air seal (“BOAS”).

5 . The first seal of claim 1 , wherein the first portion is coupled to a vane support.

6 . The first seal of claim 1 , wherein the second portion is coupled to a first a blade outer air seal (“BOAS”) support.

7 . The first seal of claim 1 , wherein the first seal enables a radial translation of a blade outer air seal (“BOAS”) in response to an aircraft maneuver.

8 . A blade outer air seal (“BOAS”) comprising:
a plurality of bleed apertures that vent compressed air over a turbine stage to cool the turbine stage during operation,
wherein the BOAS is coupled to a first seal that enables a radial translation of the BOAS, and
wherein the BOAS is coupled to a second seal that further enables the radial translation of the BOAS.

9 . The BOAS of claim 8 , wherein the first seal comprises a first portion slidably coupled to a second portion.

10 . The BOAS of claim 9 , wherein the first portion comprises a first channel that slidably receives a first projection extending from the second portion.

11 . The BOAS of claim 10 , wherein the first portion comprises a second channel that slidably receives a second projection extending from the second portion.

12 . The BOAS of claim 8 , wherein the first seal is coated with a low friction substance.

13 . The BOAS of claim 8 , wherein the second seal is coated with a low friction substance.

14 . The BOAS of claim 8 , wherein at least one of the first seal or the second seal is coated with at least one of Titanium Nitride (TiN), Titanium Aluminum Nitride, and a solid lubricant filled with nickel (Ni).

15 . A turbine stage of a turbine section of a gas turbine engine comprising:
a BOAS; and a first seal and a second seal,
wherein the first seal translates radially to accommodate a radial motion of the BOAS, and
wherein the second seal translates radially to accommodate the radial motion of the BOAS.

16 . The turbine stage of claim 15 , wherein the first seal comprises a first portion having a first channel and a second channel, and wherein the first seal further comprises a second portion having a first projection and a second projection, wherein the first projection slidably engages with the first channel and wherein the second projection slidably engages with the second channel.

17 . The turbine stage of claim 15 , wherein the first seal and the second seal enable control of cooling air dispensed from an air compartment to the turbine stage.

18 . The turbine stage of claim 15 , further comprising a puller that engages with the BOAS and translates the BOAS in a radial direction.

19 . The turbine stage of claim 18 , wherein the puller translates the BOAS in a radial direction based upon a motion of an aircraft.

20 . The turbine stage of claim 15 , wherein at least on of the first seal and the second seal is coated with a low friction substance.

Assignees

• United Technologies Corp

Inventors

• Strock Christopher W
• Lutjen Paul M

Classifications

• F01D25/12

  Cooling · CPC title

• F05D2300/2284

  of titanium · CPC title

• F01D17/105

  by passing part of the fluid · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title