Adjustable transition support and method of using the same

Patent metadata

Field	Value
Publication number	US-9702258-B2
Application number	US-201414321211-A
Country	US
Kind code	B2
Filing date	Jul 1, 2014
Priority date	Jul 1, 2014
Publication date	Jul 11, 2017
Grant date	Jul 11, 2017

Abstract

A gas turbine engine which has at least a combustor section and a turbine cylinder section, wherein the combustor section includes a transition piece coupled to a vane carrier assembly, wherein the vane carrier assembly includes a plurality of holes that correspond with one or more holes of the transition piece, and wherein at least one of the pluralities of holes is adapted to receive a pin-type member therein for shifting the transition piece toward an upstream or downstream end. A system and method for shifting a transition piece in a gas turbine engine includes at least moving a pin-type member from a first position to a second position, where the movement shifts the transition piece in a direction towards an upstream end or a downstream end.

First claim

We claim:

1. A gas turbine with an adjustable transition piece comprising:
at least a combustor section operatively connected to a turbine section;
wherein said combustor section includes:
a transition duct having an upstream end and a downstream end; and
a transition support coupled with said transition duct proximate to said downstream end, said transition support having a plurality of recesses for coupling said transition support to the turbine section; and
wherein said turbine section includes:
a vane carrier assembly, and wherein said vane carrier assembly is coupled to said transition support via a transition adjustable means disposed between one or more recesses of the vane carrier assembly corresponding to one or more of the plurality of recesses of said transition support for shifting said transition duct towards said upstream end or said downstream end.

2. The gas turbine of claim 1 , wherein said transition adjustable means is a pin.

3. The gas turbine of claim 2 , wherein said transition adjustable means is an eccentric pin.

4. The gas turbine of claim 3 , wherein at least a portion of said eccentric pin is threaded.

5. The gas turbine of claim 1 , wherein said transition adjustable means shifts said transition support integrally formed with said transition duct towards said upstream end.

6. The gas turbine of claim 1 , wherein said transition adjustable means shifts said transition support integrally formed with said transition duct towards said downstream end.

7. A system for adjusting a transition piece in a gas turbine comprising:
a transition piece including:
a transition duct having an upstream end for operatively connecting to a combustor section of a turbine, and a downstream end for operatively connecting to a turbine cylinder section of a turbine; and
a transition support integrally formed with said transition duct proximate to said downstream end, said transition support formed from an aft mount including a flange having one or more holes, and an exit frame;
a vane carrier assembly at least partially interfacing with said transition support, said vane carrier assembly having a plurality of holes corresponding to the one or more holes of said flange; and
a means for adjusting a transition piece at least partially received within the one or more of said plurality of holes of said vane carrier assembly and the corresponding one or more holes of the flange for shifting said transition piece.

8. The system of claim 7 , wherein the means for adjusting a transition piece is a pin.

9. The system of claim 8 , wherein the means for adjusting a transition piece is an eccentric pin.

10. The system of claim 9 , wherein at least a portion of said eccentric pin is threaded, and at least one of said holes receiving said eccentric pins includes grooves corresponding to the treaded portion.

11. The system of claim 10 , wherein the means for adjust a transition piece further includes a retaining means for removably securing said eccentric pin.

12. The system of claim 11 , wherein the retaining means is a snap ring.

13. The system of claim 7 , wherein means for adjusting a transition piece is configured to shift said transition piece toward said upstream end or said downstream end.

14. An adjustable transition piece comprising:
a transition duct having an upstream end and a downstream end;
a transition support proximate to said downstream end and including a flange adapted to interface with a vane carrier at the downstream end and including a radially extending hole positioned relative to a corresponding radially extending hole of the vane carrier when the flange interfaces with the vane carrier; and
a means for adjusting a transition piece adapted to be at least partially received through the radially extending holes of the vane carrier and flange for shifting the transition piece in an upstream or downstream direction based on a movement of the means for adjusting a transition piece.

15. The transition piece of claim 14 , wherein the transition support is integrally formed with the transition duct.

16. The transition piece of claim 14 , wherein the means for adjusting the transition piece is a pin.

17. The transition piece of claim 16 , wherein the pin is an rotatable eccentric pin.

18. The transition piece of claim 16 , further comprising a retaining means adapted to interface with the pin to restrict movement of the pin.

19. The transition piece of claim 14 , wherein at least a portion of the means for adjusting a transition piece is threaded and at least one of the radially extending holes of the vane carrier and flange includes grooves corresponding to the treaded portion of the means for adjusting a transition piece.

20. The transition piece of claim 14 , wherein at least a portion of the means for adjusting a transition piece includes an anti-rotation means.

Assignees

• Siemens Energy Inc

Inventors

• Mayer Clinton A
• Kieffer William M
• Hicks Paul G

Classifications

• F01D25/28

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

• F01D9/023 Primary

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