Anti-rotation shim seal

Patent metadata

Field	Value
Publication number	US-10450882-B2
Application number	US-201615077000-A
Country	US
Kind code	B2
Filing date	Mar 22, 2016
Priority date	Mar 22, 2016
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

An interface arrangement includes two annular components that extend along an axis and are in contact with one another and a third component that is positioned radially inward from at least one of the two components. There is an anti-rotation feature on one of the three components that engages an anti-rotation feature on an annular seal member. The seal member is in contact with the first two components and is positioned between the third component and at least one of the first two components.

First claim

The invention claimed is:

1. An interface arrangement comprising:
a first component having a first annular shape that extends along an axis;
a second component having a second annular shape that extends along the axis, the second component being in contact with the first component and extending axially from the first component;
a third component positioned radially inward of at least a first portion of the first component and at least a second portion of the second component;
a first anti-rotation feature included on the third component
a seal member having an annular shape that extends along the axis, the seal member being in contact with the first component and the second component and being positioned between the third component and at least one of the first component and the second component, the seal member including a second anti-rotation feature extending radially inward and configured to engage the first anti-rotation feature;
a third anti-rotation feature included on one of the first component and the second component;
a fourth anti-rotation feature included on the seal member and configured to engage the third anti-rotation feature;
wherein the first anti-rotation feature comprises a first plurality of lugs, the second anti-rotation feature comprises a second plurality of lugs, the third anti-rotation feature comprises a third plurality of lugs, and the fourth anti-rotation feature comprises a fourth plurality of lugs; and
wherein the first and fourth pluralities of lugs extend radially outward and the third plurality of lugs extends axially from the one of the first component and second component.

2. The interface arrangement of claim 1 , wherein the seal member comprises:
a body having a first side, a second side, a third side opposite of the first side, and a fourth side opposite of the second side;
wherein the first anti-rotation feature extends from the first side and the third anti-rotation feature extends from the third side.

3. The interface arrangement of claim 2 , wherein the first and third sides extend axially and the second and fourth sides extend radially.

4. The interface arrangement of claim 2 , wherein:
the second side is continuous and is in contact with a first continuous face of the first component; and
the fourth side is continuous and is in contact with a second continuous face of the second component.

5. The interface arrangement of claim 1 , wherein the first component is attached to the second component distal from the interface arrangement.

6. The interface arrangement of claim 1 , wherein the seal member is configured to inhibit fluid flow through the interface arrangement.

7. The interface arrangement of claim 1 , further comprising:
a second seal positioned between the second component and the third component radially inward of the seal member.

8. The interface arrangement of claim 1 , wherein the second plurality of lugs are circumferentially coincident with the fourth plurality of lugs.

9. A gas turbine engine extending along an axis, the gas turbine engine comprising:
a compressor, the compressor comprising:
a first compressor case;
a second compressor case adjacent to the first compressor case; and
a compressor component connected to one of the first and second compressor cases;

a combustor downstream of the compressor, the combustor comprising:
a combustor case adjacent to the second compressor case; and
a combustor component connected to the combustor case;

a turbine downstream of the combustor, the combustor comprising:
a first turbine case adjacent to the combustor case; a second turbine case adjacent to the first turbine case; and

a turbine component connected to one of the first and second turbine cases;
a first anti-rotation feature; and
a seal member positioned at one of the following interfaces: the first and second compressor cases, the second compressor case and the combustor case, the combustor case and the first turbine case, and the first and second turbine cases, wherein:
the seal member is positioned to interfere with relative movement between one of the compressor component, the combustor component, and the turbine component with respect to one of the first and second compressor cases, the combustor case, and the first and second turbine cases;
the seal member is positioned to block fluid flow between relative movement between one of the first and second compressor cases, the second compressor case and the combustor case, the combustor case and the first turbine case, and the first and second turbine cases;

the seal member comprises a first plurality of lugs extending radially inward and a second plurality of lugs extending radially outward;
the combustor case comprises a third plurality of lugs extending forward to engage the second plurality of lugs; and
the compressor component comprises a fourth plurality of lugs facing radially outward to engage the first plurality of lugs.

10. The gas turbine engine of claim 9 , wherein the compressor component is a compressor stator vane and the turbine component is a turbine stator vane.

11. The gas turbine engine of claim 9 , wherein the seal member further comprises:
a plurality of inner lugs configured to engage a plurality of component lugs on one of the compressor component, the combustor component, and the turbine component; and
a plurality of outer lugs configured to engage a plurality of case lugs on one of the first and second compressor cases, the second compressor case and the combustor case.

12. The gas turbine engine of claim 9 , wherein:
the compressor component is radially inside of one of the first and second compressor cases;
the combustor component is radially inside the combustor case;
the turbine component is radially inside of one of the first and second turbine cases; and
the seal member is positioned to block inhibit fluid flow from one of the compressor component, the combustor component, and the turbine component to an exterior of one of the first and second compressor cases, the combustor case, and the first and second turbine cases.

13. The gas turbine engine of claim 9 , wherein the seal member is positioned between the second compressor case and the combustor case, and wherein the compressor component is a compressor vane.

14. The gas turbine engine of claim 13 , wherein
the second compressor case and the combustor case are connected using a snap fit joint proximate to the seal member; and
the second compressor case and the combustor case are connected using a plurality of fasteners distal to the seal member.

15. The gas turbine engine of claim 13 , and further comprising:
a second seal positioned between the combustor case and the compressor component radially inward of the seal member.

16. The gas turbine engine of claim 13 , wherein the second compressor case overlaps the combustor case such that a portion of the second compressor case is directly radially outward of the combustor case.

17. The gas turbine engine of claim 13 , wherein the combustor case overlaps the compressor component such that a portion of the combustor case is directly radially outward of the compressor component.

Assignees

• United Technologies Corp

Inventors

• Ponchak Jeffrey D
• Lucier Jessica M
• Rogers Mark J

Classifications

• F05D2240/55

  Seals · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2240/58

  Piston ring seals · CPC title