Blade outer air seal having inward pointing extension

Patent metadata

Field	Value
Publication number	US-9506367-B2
Application number	US-201213554273-A
Country	US
Kind code	B2
Filing date	Jul 20, 2012
Priority date	Jul 20, 2012
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face.

First claim

What is claimed is:

1. A blade outer air seal (BOAS) for a gas turbine engine, comprising:
a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion;
a seal land that extends in a first direction relative to said seal body and includes an inward pointing extension that contacts a portion of a vane segment, said seal land and said inward pointing extension is a monolithic structure; and
a retention flange that extends in a second direction relative to said seal body, and said retention flange is a separate and distinct component from said seal land.

2. The BOAS as recited in claim 1 , wherein said retention flange includes a radially outer portion and a radially inner portion, and said radially outer portion is received within a slot of a casing of the gas turbine engine and a vane segment rests against said radially inner portion.

3. The BOAS as recited in claim 1 , wherein said retention flange is positioned radially outwardly of said seal land.

4. The BOAS as recited in claim 1 , wherein said retention flange contacts at least one support portion of said seal land.

5. The BOAS as recited in claim 4 , wherein said at least one support portion is an axially extending portion of said seal land.

6. The BOAS as recited in claim 1 , comprising a seal attached to said radially inner face of said seal body.

7. The BOAS as recited in claim 6 , wherein said seal is a honeycomb seal.

8. The BOAS as recited in claim 1 , comprising a seal that extends between said inward pointing extension and a vane segment.

9. The BOAS as recited in claim 1 , wherein a radially innermost surface of said inward pointing extension extends to a position inboard of a blade tip of a blade that rotates relative to said seal body.

10. The BOAS as recited in claim 1 , comprising a seal received within a pocket established between an aft wall of said vane segment and an upstream wall of said inward pointing extension.

11. The BOAS as recited in claim 1 , wherein a radially innermost surface of said inward pointing extension contacts said vane segment.

12. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication with said combustor section;
a blade outer air seal (BOAS) associated with at least one of said compressor section and said turbine section, wherein said BOAS includes:
a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion;
a seal land that extends from said seal body and includes an inward pointing extension that is integral with said seal land such that said seal land and said inward pointing extension is a monolithic structure; and
a retention flange that retains said BOAS relative to a casing of the gas turbine engine, said retention flange supported by said seal land at least at two different radial locations of said retention flange, said seal land in physical contact with a radially inner surface of said retention flange at said at least two different radial locations.

13. The gas turbine engine as recited in claim 12 , wherein a radially innermost surface of said inward pointing extension extends to a position inboard of a blade tip of a blade of one of said compressor section and said turbine section.

14. The gas turbine engine as recited in claim 12 , wherein said retention flange includes a radially outer portion and a radially inner portion, and said radially outer portion is received within a slot of said casing and a vane segment of one of said compressor section and said turbine section rests against said radially inner portion.

15. The gas turbine engine as recited in claim 12 , comprising a seal that extends within a pocket between said inward pointing extension and a vane segment.

16. The gas turbine engine as recited in claim 15 , wherein at least a portion of said retention flange extends radially outwardly from said seal.

17. A method of incorporating a blade outer air seal (BOAS) for use in a gas turbine engine, comprising:
positioning a seal axially between a vane segment of the gas turbine engine and an inward pointing extension of a seal land of the BOAS such that the seal abuts both the vane segment and the inward pointing extension; and
supporting a retention flange of the BOAS with the seal land to radially support the vane segment, the retention flange supported at two different radial locations of the retention flange such that the seal land is in physical contact with a radially inner surface of the retention flange at the two different radial locations.

18. The method as recited in claim 17 , comprising:
blocking hot combustion gases from escaping a core flow path of the gas turbine engine with the seal land.

19. The method as recited in claim 18 , wherein the step of blocking includes shielding the vane segment with the inward pointing extension of the seal land.

20. The method as recited in claim 17 , wherein the step of supporting includes positioning at least one support portion of the seal land radially inwardly from the retention flange.

21. The method as recited in claim 17 , wherein a radially outer portion of the retention flange is received within a slot of a casing that surrounds the BOAS and the vane segment rests against a radially inner portion of the retention flange.

22. The method as recited in claim 17 , wherein the seal abuts against an upstream wall of the inward pointing extension.

Assignees

• Clouse Brian Ellis
• United Technologies Corp

Inventors

• Clouse Brian Ellis

Classifications

• Y10T29/49297

  Seal or packing making · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title