Blade outer air seal for a gas turbine engine

• US 8,998,572 B2
• Filed: 06/04/2012
• Issued: 04/07/2015
• Est. Priority Date: 06/04/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Lutjen, Paul M., Dabbs, Thurman Carlo
• Primary Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US13/487,347
• Publication Number:
  US 20130323032A1
• Time in Patent Office: 1,037 Days
• Field of Search: 415/173.1, 415/174.1
• US Class Current: 415/173.1
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F04D 29/526 Details of the casing section radially opposing blade tips ducts F04D29/545
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

Claims

1. A blade outer air seal (BOAS) segment, comprising:

a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face; and

at least one of said first mate face and said second mate face including an inner wall having a ledge that protrudes from said inner wall and an undercut passage radially inward from said ledge and that extends uninterrupted along a length of said ledge, said ledge further extending along an inner wall of at least one of said leading edge face and said trailing edge face.

2. The BOAS segment as recited in claim 1, wherein said undercut passage is in fluid communication with a core cavity of said seal body.

3. The BOAS segment as recited in claim 2, wherein said core cavity extends between said radially outer surface and a cover plate received against said ledge.

4. The BOAS segment as recited in claim 1, comprising at least one cooling hole that extends through said ledge.

5. The BOAS segment as recited in claim 4, wherein said at least one cooling hole receives a secondary cooling airflow to impingement cool an edge portion of a core cavity of said seal body.

6. The BOAS segment as recited in claim 1, wherein an edge portion of said undercut passage is circumferentially offset from said inner wall in a direction away from a core cavity of said seal body.

7. The BOAS segment as recited in claim 1, comprising:

a cooling hole formed through said ledge and opening into said undercut passage; and

a hole extending between an edge portion of said undercut passage and an exterior wall of said at least one of said first mate face and said second mate face that includes said ledge, wherein a secondary cooling airflow path extends through said cooling hole, into said undercut passage, and then through said hole.

8. A blade outer air seal (BOAS) assembly, comprising:

a BOAS segment having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face;

a cover plate received at said radially outer face such that a core cavity extends between said radially outer face and said cover plate;

wherein at least one of said first mate face and said second mate face include a ledge that protrudes from an inner wall to support said cover plate and an undercut passage radially inward from said ledge, wherein said core cavity extends to an edge portion of said undercut passage that is circumferentially offset from said inner wall in a direction away from said core cavity;

a cooling hole formed through said ledge and opening into said undercut passage; and

a hole extending between said edge portion and an exterior wall of said at least one of said first mate face and said second mate face that includes said ledge, wherein a secondary cooling airflow path extends through said cooling hole, into said undercut passage, and then through said hole.

9. The BOAS assembly as recited in claim 8, wherein said ledge extends from said first mate face and said edge portion is circumferentially offset from said inner wall in a direction toward said first mate face.

10. The BOAS assembly as recited in claim 8, wherein said cooling hole is positioned between said cover plate and said inner wall.

11. The BOAS assembly as recited in claim 8, wherein said cover plate includes at least one hole.

12. The BOAS assembly as recited in claim 8, wherein said cover plate is metallurgically bonded to said ledge.

13. The BOAS assembly as recited in claim 8, wherein at least one of said first mate face and said second mate face includes a plurality of holes that extend through said edge portion.

14. The BOAS assembly as recited in claim 13, wherein said undercut passage extends uninterrupted along a length of said edge portion.

15. The BOAS assembly as recited in claim 8, wherein said undercut passage extends uninterrupted between a rib and at least one of said leading edge face and said trailing edge face.

16. The BOAS assembly as recited in claim 8, wherein said ledge extends along an inner wall of at least one of said leading edge face and said trailing edge face.

17. 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) assembly associated with at least one of said compressor section and said turbine section, wherein said BOAS assembly includes a plurality of BOAS segments having;

a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face; and

wherein at least one of said first mate face and said second mate face include an inner wall having a ledge that protrudes from said inner wall and an undercut passage radially inward from said ledge, said ledge further extending along an inner wall of at least one of said leading edge face and said trailing edge face, wherein a core cavity extends to an edge portion of said undercut passage that is circumferentially offset from said inner wall in a direction away from said core cavity.

18. The gas turbine engine as recited in claim 17, comprising a cover plate received at said radially outer face such that said core cavity extends radially between said radially outer face and said cover plate.

19. The gas turbine engine as recited in claim 18, comprising at least one cooling hole through said ledge and positioned between said cover plate and said inner wall.

20. The gas turbine engine as recited in claim 17, wherein said undercut passage extends uninterrupted along a length of said ledge.

21. The gas turbine engine as recited in claim 17, comprising a cavity radially outward from said BOAS assembly, wherein a secondary cooling airflow is communicated from said cavity to said core cavity.

22. The gas turbine engine as recited in claim 17, wherein each of said first mate face and said second mate face include said ledge.