Low leakage multi-directional interface for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9879558-B2
Application number	US-201414766469-A
Country	US
Kind code	B2
Filing date	Feb 5, 2014
Priority date	Feb 7, 2013
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

First claim

What is claimed is:

1. An interface within a gas turbine engine, comprising:
a multiple of segmented components, each with a segment flange with a multiple of segment apertures, at least one of said multiple of segment apertures includes a first slot aperture; and
a full ring component with a ring flange that defines a multiple of ring apertures, at least one of said multiple of ring apertures includes a second slot aperture, said second slot aperture transverse to said first slot aperture.

2. The interface as recited in claim 1 , wherein said second slot aperture is perpendicular to said first slot aperture.

3. The interface as recited in claim 1 , wherein said first slot aperture is circumferentially oriented.

4. The interface as recited in claim 1 , wherein said second slot aperture is radially oriented.

5. The interface as recited in claim 1 , wherein said first slot aperture is circumferentially oriented and said second slot aperture is radially oriented.

6. The interface as recited in claim 1 , wherein each of said multiple of segmented components are Blade Outer Air Seal (BOAS) segments.

7. The interface as recited in claim 1 , wherein said full ring component is a full ring seal support.

8. The interface as recited in claim 1 , further comprising a case flange adjacent to said segment flange of each of said multiple of segmented components.

9. The interface as recited in claim 8 , further comprising a multiple of fastener assemblies mounted through said case flange, said multiple of segment apertures and said multiple of ring apertures.

10. The interface as recited in claim 9 , wherein each of said multiple of fastener assemblies include a flanged bushing that abuts said case flange and extends through said ring flange and said segment flange.

11. A Blade Outer Air Seal (BOAS) assembly within a gas turbine engine, comprising:
a multiple of Blade Outer Air Seal (BOAS) segments, each with a segment flange with a multiple of segment apertures, at least one of said multiple of segment apertures includes a first slot aperture; and
a full ring seal support with a ring flange that defines a multiple of ring apertures, at least one of said multiple of ring apertures includes a second slot aperture, said second slot aperture transverse to said first slot aperture.

12. The interface as recited in claim 11 , wherein said multiple of segment apertures includes a circular aperture.

13. The interface as recited in claim 11 , wherein said multiple of segment apertures defines a slot aperture, circular aperture, slot aperture sequence.

14. The interface as recited in claim 13 , wherein said circular aperture is circumferentially centrally located in said segment flange.

15. The interface as recited in claim 11 , wherein said first slot aperture is circumferentially oriented and said second slot aperture is radially oriented.

16. The interface as recited in claim 11 , further comprising a case flange adjacent to said segment flange of each of said multiple of segmented components.

17. The interface as recited in claim 16 , further comprising a multiple of fastener assemblies mounted through said case flange, said multiple of segment apertures and said multiple of ring apertures.

18. The interface as recited in claim 17 , wherein each of said multiple of fastener assemblies include a flanged bushing that abuts said case flange and extends through said ring flange and said segment flange.

19. A method of mounting a Blade Outer Air Seal (BOAS) segment within a gas turbine engine, comprising:
mounting a fastener assembly through a first slot aperture in a segment flange of a Blade Outer Air Seal (BOAS) segment, the first slot aperture transverse to a second slot aperture in a ring flange of a full ring seal support.

20. The method as recited in claim 19 , further comprising locating a flanged bushing of the fastener assembly through the first slot aperture and the second slot aperture to abut a case flange.

Assignees

• United Technologies Corp

Inventors

• Rogers Mark J
• Broomer Mark
• Mcgarrah Craig R
• Davis Timothy M
• Swift Anthony B
• Keene Russell E
• Roy Thill Carson A
• Dunbar Timothy A

Classifications

• F05D2240/55

  Seals · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/20

  Rotors · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2240/10

  Stators · CPC title