Method and tool for installation of a transition duct

Patent metadata

Field	Value
Publication number	US-9709276-B2
Application number	US-201414471553-A
Country	US
Kind code	B2
Filing date	Aug 28, 2014
Priority date	Aug 28, 2014
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section.

First claim

What is claimed is:

1. A method for installation of a transition duct in a gas turbine engine, comprising:
positioning a guide structure extending in an inclined direction with respect to a gas turbine axis, wherein at least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine,
engaging the transition duct with the guide structure such that the transition duct is movable along the guide structure, and
imparting a motion to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end portion of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section,
wherein an aft frame of the transition duct comprises attachment structures, each attachments structure having a link with a tangential pin that engages in a respective slot on the forward face of the stator,
wherein each pin is rotatable about a tangential axis, such that said motion transitions from the inclined direction in relation to the turbine axis to an axial direction in relation to the turbine axis facilitated by the rotation of the pins about the tangential axis.

2. The method according to claim 1 , wherein the guide structure comprises a track or a rail.

3. The method according to claim 1 , wherein the transition duct is engaged slidably to the guide structure.

4. The method according to claim 3 , wherein the transition duct is provided with a bracket on an outer surface of the transition duct, for slidably engaging with the guide structure.

5. The method according to claim 4 , wherein the bracket is disposed at a location that corresponds to a center of mass of the transition duct.

6. The method according to claim 1 , wherein the guide structure is positioned by securing the guide structure to the combustor section.

7. The method according to claim 6 , wherein the guide structure is secured to a sleeve of a combustor in the combustor section.

8. The method according to claim 7 , wherein the guide structure comprises a pair or rails or tracks that are positioned by attaching said rails or tracks to diametrically opposite sides of the combustor sleeve.

9. The method according to claim 8 , wherein a first attachment point of the sleeve with the rails or tracks is located at an outboard end of the sleeve.

10. The method according to claim 8 , wherein a second attachment point of the sleeve with the rails or tracks is located at a bore in a case provided for a cross-over tube of the combustor section.

11. The method according to claim 8 , wherein after being positioned, the aft ends of the rails or tracks extend beyond the sleeve of the combustor.

12. The method according to claim 1 , further comprising bolting the aft end portion of the transition duct to the forward face of the stator component of the turbine section after the transition duct is moved along the guide track to said installed position.

13. The method according to claim 12 , further comprising removing the rails after aft end portion of the transition duct has been bolted to the forward face of the stator component of the turbine section.

14. The method according to claim 1 , wherein the stator component is a turbine vane carrier.

Assignees

• Siemens Energy Inc

Inventors

• Pankey William W

Classifications

• F05D2230/68

  using auxiliary equipment for lifting or holding · CPC title

• B23P2700/13

  Parts of turbine combustion chambers · CPC title

• F23R3/02 Primary

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · 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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title