Support arrangement for a transition piece of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9574460-B2
Application number	US-201414527860-A
Country	US
Kind code	B2
Filing date	Oct 30, 2014
Priority date	Oct 30, 2014
Publication date	Feb 21, 2017
Grant date	Feb 21, 2017

Abstract

A support arrangement ( 10 ) for a transition piece ( 12 ) of a gas turbine engine ( 14 ). The support arrangement includes a mounting bracket ( 16 ) for the transition piece and a pin ( 18 ) supporting the mounting bracket in an interior ( 20 ) of the gas turbine engine and extending through an opening ( 22 ) in a casing ( 24 ) to an exterior ( 26 ) of the gas turbine engine. The support arrangement further includes a spherical washer ( 28, 38 ) positioned between the pin and either the mounting bracket or the casing.

First claim

The invention claimed is:

1. A support arrangement for a transition piece of a gas turbine engine, the support arrangement comprising:
a mounting bracket for the transition piece;
a pin supporting the mounting bracket in an interior of the gas turbine engine and extending through an opening in a casing of the gas turbine engine to an exterior of the gas turbine engine; and
a spherical washer positioned between the pin and one of the mounting bracket and the casing.

2. The support arrangement of claim 1 , wherein the spherical washer is positioned between the pin and an exterior side of the casing, said support arrangement further comprising a second spherical washer positioned between the pin and an interior side of the casing.

3. The support arrangement of claim 1 , wherein the pin extends through an opening in the mounting bracket, wherein the spherical washer is positioned between the pin and a first side of the mounting bracket, said support arrangement further comprising a second spherical washer positioned between the pin and a second side of the mounting bracket opposite to the first side.

4. The support arrangement of claim 3 , wherein the opening in the mounting bracket is sized to include a gap between the pin and the mounting bracket and wherein the pin is movable within the opening, to vary an alignment of the transition piece relative to the casing.

5. The support arrangement of claim 1 , further comprising a fastener configured to tighten the pin relative to the spherical washer to maintain an alignment of the transition piece relative to the casing.

6. The support arrangement of claim 5 , wherein the fastener is positioned on an exterior side of the casing.

7. The support arrangement of claim 6 , wherein the opening is sized to include a gap between the pin and the casing, and wherein the pin is movable within the opening from the exterior of the gas turbine engine to vary the alignment of the transition piece in a circumferential plane of an end of the transition piece.

8. The support arrangement of claim 7 , wherein the pin is rotatable about an axis orthogonal to a longitudinal axis of the pin.

9. The support arrangement of claim 7 , wherein the pin is rotatable about a longitudinal axis of the pin.

10. The support arrangement of claim 1 , further comprising a fastener positioned on an interior side of the casing, wherein an axial position of the fastener relative to the pin is adjustable from the exterior of the gas turbine engine to vary an axial location of the transition piece relative to the casing.

11. The support arrangement of claim 10 , wherein the pin includes an outer shaft threadably secured to the fastener and an inner shaft rotatably coupled to the mounting bracket; wherein the axial position of the fastener relative to the pin is adjustable based on relative rotation between the outer shaft and the fastener initiated from the exterior of the gas turbine engine.

12. A gas turbine engine comprising:
a casing;
a transition piece;
a mounting bracket for the transition piece; and
a pin supporting the mounting bracket in an interior of the gas turbine engine and extending through an opening in the casing to an exterior of the gas turbine engine;
wherein the pin is movable within the opening from the exterior of the gas turbine engine to vary an alignment of the transition piece relative to the casing.

13. The gas turbine engine of claim 12 , wherein the pin is rotatable about an axis orthogonal to a longitudinal axis of the pin.

14. The gas turbine engine of claim 12 , wherein the pin is rotatable about a longitudinal axis of the pin.

15. The gas turbine engine of claim 12 , further comprising a spherical washer positioned between the pin and one of the mounting bracket and the casing.

16. The gas turbine engine of claim 15 , wherein the spherical washer is positioned between the pin and an exterior side of the casing, said gas turbine engine further comprising a second spherical washer positioned between the pin and an interior side of the casing.

17. The gas turbine engine of claim 15 , wherein the pin extends through an opening in the mounting bracket, wherein the spherical washer is positioned between the pin and a first side of the mounting bracket, said gas turbine engine further comprising a second spherical washer positioned between the pin and a second side of the mounting bracket opposite to the first side.

18. The gas turbine engine of claim 15 , further comprising a fastener configured to tighten the pin relative to the spherical washer to maintain the alignment of the transition piece relative to the casing.

19. A support arrangement for a transition piece of a gas turbine engine, the support arrangement comprising:
a mounting bracket for the transition piece;
a pin supporting the mounting bracket in an interior of the gas turbine engine and extending through an opening in a casing to an exterior of the gas turbine engine;
a spherical washer positioned between the pin and one of the mounting bracket and the casing; and
a fastener configured to tighten the pin relative to the spherical washer to maintain an alignment of the transition piece relative to the casing.

20. The support arrangement of claim 19 , wherein the fastener is positioned on an exterior side of the casing and wherein the opening in the casing is sized to include a gap between the pin and the casing such that the pin is rotatable within the opening from the exterior of the gas turbine engine to vary the alignment of the transition piece in a circumferential plane of an end of the transition piece.

Assignees

• Siemens Energy Inc

Inventors

• Carlson Andrew
• Pankey William W

Classifications

• F05D2250/241

  spherical · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title