Gas turbine engine component having variable width feather seal slot

Patent metadata

Field	Value
Publication number	US-10072517-B2
Application number	US-201414769210-A
Country	US
Kind code	B2
Filing date	Mar 6, 2014
Priority date	Mar 8, 2013
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a mate face; and
a feather seal slot axially extending along said mate face, said feather seal slot having a variable width along a portion of its axial length;
wherein said feather seal slot includes a first axial slot portion of a first width, a second axial slot portion of a second width, and radial slot portion between said first axial slot portion and said second axial slot portion; and
wherein said second width of said second slot portion is different from said first width of said first axial slot portion;
wherein a radially extending step is formed before said first axial slot portion and said second axial slot portion.

2. The component as recited in claim 1 , wherein said component is a vane.

3. The component as recited in claim 2 , wherein said vane is a turbine vane.

4. The component as recited in claim 1 , wherein said mate face is part of a platform.

5. The component as recited in claim 1 , wherein said component is part of a blade outer air seal (BOAS).

6. The component as recited in claim 1 , wherein said second width is smaller than said first width.

7. The component as recited in claim 1 , wherein said first axial slot portion extends upstream of said radial slot portion and said second axial slot portion extends downstream of said radial slot portion.

8. The component as recited in claim 1 , comprising a feather seal received within said feather seal slot.

9. The component as recited in claim 1 , comprising a first feather seal and a second feather seal received within said feather seal slot.

10. The component as recited in claim 9 , wherein said first feather seal extends within said first axial slot portion and said second axial slot portion of said feather seal slot, and said second feather seal extends within said first axial slot portion but not within said second axial slot portion.

11. A gas turbine engine, comprising:
a first component having a first mate face;
a second component having a second mate face circumferentially adjacent to said first mate face of said first component;
wherein at least one of said first mate face and said second mate face include a feather seal slot having a first axial slot portion of a first width, a second axial slot portion of a second width, and a radial slot portion that intersects said feather seal slot between said first axial slot portion and said second slot portion;
wherein said second width of said second slot portion is different from said first width of said first slot portion;
wherein a radially extending step is formed between said first slot portion and said second slot portion; and
at least one feather seal received within said feather seal slot.

12. The gas turbine engine as recited in claim 11 , wherein said at least one feather seal includes a first feather seal and a second feather seal.

13. The gas turbine engine as recited in claim 12 , wherein a bent portion of said second feather seal extends into said radial slot portion of said feather seal slot.

14. A method of sealing between adjacent components of a gas turbine engine, comprising the steps of:
forming a feather seal slot having a variable width in a mate face of a component;
positioning at least one feather seal within the feather seal slot;
wherein the step of forming includes forming the feather seal slot to include a first axial slot portion of a first width and a second axial slot portion of a second width that is smaller than the first width;
wherein a radially extending step is formed between the first axial slot portion and the second axial slot portion; and

wherein the step of forming includes intersecting between the first axial slot portion and the second axial slot portion with a radial slot portion of the feather seal slot.

15. The method as recited in claim 14 , wherein the step of positioning includes:
loading a first feather seal into the first axial slot portion and the second axial slot portion of the feather seal slot; and
loading a second feather seal into the first axial slot portion but not the second axial slot portion.

16. The component as recited in claim 10 , wherein a bent portion of said second feather seal extends into said radial slot portion of said feather seal slot such that said second feather seal abuts against a radially extending wall of said radial slot portion that defines said radially extending step.

17. The component as recited in claim 16 , wherein said first axial slot portion is defined by an outer wall and an opposed inner wall that each extend from a first end to a second end, said first end adjacent to a leading edge of said mate face, and said second end terminating at said radial slot portion.

18. The gas turbine engine as recited in claim 13 , wherein said second width is smaller than said first width.

19. The gas turbine engine as recited in claim 18 , wherein first axial slot portion is defined by an outer wall and an opposed inner wall that each extend from a first end to a second end, said first end adjacent to a leading edge of said at least one of said first mate face and said second mate face, and said second end terminating at said radial slot portion.

20. The method as recited in claim 14 , wherein:
a bent portion of said second feather seal extends into said radial slot portion of said feather seal slot such that said second feather seal abuts against a radially extending wall of said radial slot portion that defines said radially extending step;
said first axial slot portion is defined by an outer wall and an opposed inner wall that each extend from a first end to a second end, said first end adjacent to a leading edge of said mate face, and said second end terminating at said radial slot portion; and
said component includes an airfoil extending from a platform that defines said mate face.

Assignees

• United Technologies Corp

Inventors

• Boeke Mark A
• Rajchel Kevin
• Salzillo Richard M
• Degray Jeffrey J
• Mainelli Allison

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/57

  Leaf seals · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title