Thin seal for an engine

Patent metadata

Field	Value
Publication number	US-2017211401-A1
Application number	US-201615004591-A
Country	US
Kind code	A1
Filing date	Jan 22, 2016
Priority date	Jan 22, 2016
Publication date	Jul 27, 2017
Grant date	—

Abstract

Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

First claim

1 . A method for forming a seal configured to interface with at least a first component and a second component of a gas turbine engine, the method comprising:
obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element; and processing the ingot to generate a sheet of the material, wherein the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

2 . The method of claim 1 , wherein the sheet is substantially shaped as at least one of a rectangle or a cube.

3 . The method of claim 1 , wherein the material includes nickel.

4 . The method of claim 1 , wherein the processing of the ingot includes applying an electro discharge machining technique.

5 . The method of claim 1 , wherein the processing of the ingot includes applying an abrasive material cutting technique.

6 . The method of claim 1 , wherein the processing of the ingot includes applying a blasting technique.

7 . The method of claim 1 , wherein at least one of the obtaining or the processing includes applying a casting technique.

8 . The method of claim 1 , wherein the processing of the ingot includes applying a rolling technique.

9 . The method of claim 8 , wherein application of the rolling technique provides a flat, single curve, or compound curve sheet.

10 . The method of claim 1 , further comprising:
forming a notch or slot in the sheet to accommodate an interface associated with at least one of the first component or the second component.

11 . The method of claim 1 , further comprising:
forming an arc or bent tab in the sheet.

12 . The method of claim 1 , further comprising:
applying at least one of a thermal barrier coating or an oxidation resistant metallic coating to the sheet in forming the seal.

13 . The method of claim 1 , wherein the metallic or refractory element includes at least one of Ti, Ta, or Nb.

14 . A system associated with a gas turbine engine, the system comprising:
a seal configured to interface at least a first component and a second component, the seal formed from a sheet of a single crystal material, the sheet having a thickness within a range of 0.010 inches and 0.050 inches inclusive.

15 . The system of claim 14 , further comprising:
the first component and the second component.

16 . The system of claim 15 , wherein the first component includes at least one of: a static turbine airfoil, a rotating turbine airfoil, or a segmented blade outer air seal.

17 . The system of claim 15 , wherein the first component includes at least one of: a platform, a mate face, a buttress, a spindle, a boss, a rail, or a hook.

18 . The system of claim 14 , wherein the seal includes one or more notches, slots, tabs, or arcs to accommodate interfaces associated with at least one of the first component, the second component, or a second seal.

19 . The system of claim 14 , wherein the seal is configured to accommodate operation within the engine at least at a temperature of 2000 degrees Fahrenheit.

Assignees

• United Technologies Corp

Inventors

• Cetel Alan D
• Shah Dilip M
• Hudson Eric A
• Surace Raymond

Classifications

• C22C19/00 Primary

  Alloys based on nickel or cobalt · CPC title

• F05D2230/26

  by rolling · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2230/10

  by removing material · CPC title