Additive manufactured inseparable platform damper and seal assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9863257-B2
Application number	US-201514613724-A
Country	US
Kind code	B2
Filing date	Feb 4, 2015
Priority date	Feb 4, 2015
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.

First claim

What is claimed is:

1. A damper-seal assembly for a gas turbine engine comprising:
an additively manufactured seal that forms a damper retention area; and
an additively manufactured damper entrapped in the damper retention area to form an inseparable assembly with said additively manufactured seal.

2. The assembly as recited in claim 1 , wherein said additively manufactured seal includes a first strap that extends generally flush with a top surface of said additively manufactured seal.

3. The assembly as recited in claim 2 , further comprising a second strap and a third strap generally parallel to said first strap and displaced therefrom, to form the damper retention area generally therebetween.

4. The assembly as recited in claim 2 , wherein said additively manufactured damper includes a platform rub surface with a groove formed therein opposite an undersurface of a main body, said groove at least partially receives said first strap.

5. The assembly as recited in claim 4 , further comprising a first wing and a second wing that extend from said main body generally parallel to said groove and are of a length greater than that of said damper retention area.

6. The assembly as recited in claim 1 , wherein said additively manufactured damper is assembled to said seal to slide relative thereto.

7. The assembly as recited in claim 1 , wherein said additively manufactured damper is generally “H” shaped.

8. The assembly as recited in claim 1 , wherein said additively manufactured seal has non-constant thickness.

9. The assembly as recited in claim 1 , wherein said additively manufactured seal conforms to a cavity within a turbine blade.

10. A damper-seal assembly for a gas turbine engine comprising:
a damper inseparably assembled with a seal, at least one of said seal and said damper additively manufactured.

11. The assembly as recited in claim 10 , wherein said seal includes a first strap received within a groove in said damper.

12. The assembly as recited in claim 10 , wherein said seal includes a first strap, a second strap, and a third strap, said second strap and said third strap generally parallel to said first strap and displaced therefrom to form a damper retention area generally therebetween for entrapment of said damper.

13. The assembly as recited in claim 10 , wherein said damper includes a platform rub surface with a groove formed therein opposite an undersurface of a main body, said groove at least partially receives a first strap of said damper, a second strap, and a third strap, generally parallel to said first strap for entrapment of said damper within a damper retention area.

14. The assembly as recited in claim 13 , further comprising a first wing and a second wing that extend from said main body generally parallel to said groove and are of a length greater than that of said damper retention area.

15. The assembly as recited in claim 10 , wherein said additively manufactured damper is assembled to said seal to slide relative thereto.

16. A turbine assembly comprising:
a first turbine blade circumferentially adjacent to a second turbine blade, said first turbine blade includes a first platform with a first underplatform surface, said second turbine blade includes a second platform with a second underplatform surface, said first underplatform surface and said second underplatform surface at least partially defines a cavity;
an additively manufactured damper additively manufactured onto a sheet metal seal, said additively manufactured damper interfaces with said first underplatform surface and said second underplatform surface, said additively manufactured damper entrapped in said sheet metal seal to form an inseparable assembly.

17. The assembly as recited in claim 16 , wherein said additively manufactured damper is assembled to said seal to slide relative thereto.

18. The assembly as recited in claim 17 , wherein said additively manufactured seal includes a first strap that extends generally flush with a top surface of said additively manufactured seal.

19. The assembly as recited in claim 18 , further comprising a second strap and a third strap generally parallel to said first strap and displaced therefrom to form a damper retention area generally therebetween for entrapment of said additively manufactured damper.

20. The assembly as recited in claim 19 , wherein said additively manufactured damper includes a platform rub surface with a groove formed therein opposite an undersurface of a main body, said groove at least partially receives said first strap.

21. The assembly as recited in claim 10 , wherein said additively manufactured damper is additively manufactured onto a sheet metal seal.

22. A damper-seal assembly for a gas turbine engine comprising: an additively manufactured seal comprising a first strap, a second strap and a third strap that forms a damper retention area; and an additively manufactured damper comprising a platform rub surface with a groove formed therein opposite an undersurface of a main body, the groove receives the first strap, a first wing, and a second wing extends from said main body generally parallel to said groove, said first wind and said second wing of a length greater than that of a damper retention area that receives the second strap and the third strap such that said additively manufactured damper is entrapped in the damper retention area to form an inseparable assembly with said additively manufactured seal.

Assignees

• United Technologies Corp

Inventors

• Snyder Daniel A
• Otero Edwin
• Kironn Lexia
• Twelves Jr Wendell V
• Butcher Evan

Classifications

• B22F10/20

  Direct sintering or melting · CPC title

• F05D2230/22

  by sintering · CPC title

• B29C64/153

  using layers of powder being selectively joined, e.g. by selective laser sintering or melting · CPC title

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• B22F7/00

  Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting {wherein at least one part is obtained by sintering or compression (application of coating layers by use of metal powders, see C23C)} · CPC title