Flexible feather seal for blade outer air seal gas turbine engine rapid response clearance control system

Patent metadata

Field	Value
Publication number	US-9915162-B2
Application number	US-201414780872-A
Country	US
Kind code	B2
Filing date	Feb 6, 2014
Priority date	Apr 12, 2013
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

An active clearance control system for a gas turbine engine includes an intersegment seal engaged with each pair of a multiple of air seal segments.

First claim

What is claimed is:

1. An active clearance control system for a gas turbine engine comprising:
a multiple of air seal segments;
a intersegment seal engaged with each pair of said multiple of air seal segments; and
a secondary intersegment seal engageable with said intersegment seal,
wherein said intersegment seal includes a head from which a flange extends,
wherein said secondary intersegment seal includes a radially extending wall,
wherein said radially extending wall circumferentially exceeds a circumferential span of the flange, and
wherein said intersegment seal is in the shape of the Greek letter Omega.

2. The system as recited in claim 1 , wherein said intersegment seal is received within an intersegment slot between each pair of said multiple of air seal segments.

3. The system as recited in claim 2 , wherein said intersegment slot includes an inner slot portion and an outer slot portion with respect to a central longitudinal engine axis in each of said multiple of air seal segments.

4. The system as recited in claim 2 , wherein said intersegment slot between each pair of said multiple of air seal segments is generally “top-hat” shaped.

5. The system as recited in claim 1 , wherein said secondary intersegment seal is at least partially recessed within an axial face of each pair of said multiple of air seal segments.

6. The system as recited in claim 1 , wherein axially extended legs extend from said radially extending wall along said intersegment seal.

7. The system as recited in claim 1 , wherein axially extended legs extend from said radially extending wall along the flange.

8. The system as recited in claim 1 , wherein said secondary intersegment seal includes the radially extending wall with a barrier adjacent to a head of said intersegment seal.

9. A method of active blade tip clearance control for a gas turbine engine, comprising:
locating an intersegment seal between each pair of a multiple of air seal segments; and
sealing the intersegment seal with a secondary intersegment seal,
wherein said intersegment seal includes a head from which a flange extends,
wherein said secondary intersegment seal includes a radially extending wall,
wherein said radially extending wall circumferentially exceeds a circumferential span of the flange, and
wherein the intersegment seal is in the shape of the Greek letter Omega.

10. The system as recited in claim 1 , wherein said radially extending wall traverses a thickness of the flange in the radial direction.

11. The method as recited in claim 9 , wherein said radially extending wall traverses a thickness of the flange in the radial direction.

Assignees

• United Technologies Corp

Inventors

• Duguay Brian

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/57

  Leaf seals · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F16J15/445

  with means for adjusting the clearance · CPC title

• F01D11/20 Primary

  Actively adjusting tip-clearance · CPC title