Combustion liner assembly having a mount stake coupled to an upstream support

Patent metadata

Field	Value
Publication number	US-9046272-B2
Application number	US-62534909-A
Country	US
Kind code	B2
Filing date	Nov 24, 2009
Priority date	Dec 31, 2008
Publication date	Jun 2, 2015
Grant date	Jun 2, 2015

Abstract

A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool.

First claim

What is claimed is:

1. An apparatus comprising:
a gas turbine engine including a combustor having an inner casing, an outer casing, an inner liner, and an outer liner, a combustion passage formed between the inner liner and outer liner, an inner passage formed between the inner casing and the inner liner, and an outer passage formed between the outer casing and the outer liner, wherein the inner liner includes an inner liner opening, the outer liner includes an outer liner opening;
a mount stake that is elongate and radially extending between and coupling the inner liner to the outer liner, the mount stake having a first end and a second end and having a length longer than any dimension of a cross section taken along the length, the mount stake being circumferentially spaced from a neighboring mount stake such that a flow space is formed therebetween, at least one of the first end and second end failing to fully extend across one of the inner passage and the outer passage, where the mount stake is positioned such that is reaches through the inner liner opening and the outer liner opening; and
a combustor support that extends upstream of the mount stake and is anchored with the gas turbine engine and extends into the combustor, the combustor support coupled to the mount stake intermediate the first end and the second end,
further including a support spool coupled to the combustor support, and wherein the support spool is directly coupled to the mount stake.

2. The apparatus of claim 1 , wherein the combustor support includes an opening through which the mount stake is received.

3. The apparatus of claim 1 , wherein the gas turbine engine further includes a diffuser connected to the combustor support.

4. The apparatus of claim 1 , wherein the support spool includes a passageway capable of receiving the mount stake.

5. The apparatus of claim 4 , wherein the combustor support and support spool are separable, and which further includes an alignment device structured to position the support spool relative to the combustor support.

6. The apparatus of claim 1 , wherein the combustor support includes a separable first portion and second portion, the first and second portion indexable relative to each other.

7. The apparatus of claim 1 , wherein the combustor support is anchored with a diffuser.

8. An apparatus comprising:
a gas turbine engine having a compressor that provides a compressed working fluid to a diffuser downstream of the compressor,
the gas turbine engine also having a casing located near the outer liner and a mount stake that is elongate and radially traversing between inner and outer liners of a combustor and having a radial length larger than any dimension of a cross section taken along the radial length, the mount stake being circumferentially spaced from an adjacent mount stake such that an open flow space is created therebetween, and wherein the mount stake fails to contact the casing,
the mount stake having an intermediate portion coupled to a support that extends upstream of the mount stake toward the diffuser and between the inner and outer liners,
wherein the mount stake directly connects the inner and outer liners,
wherein the support includes a support spool, and wherein the support spool is directly coupled to the mount stake.

9. The apparatus of claim 8 , wherein the support includes an opening operable to receive the mount stake.

10. The apparatus of claim 9 , wherein the support includes a support bracket coupled to the support spool.

11. The apparatus of claim 10 , wherein the support spool is structured to slidingly receive the mount stake.

12. The apparatus of claim 8 , wherein the support is connected to the diffuser.

13. The apparatus of claim 8 , which further includes a locating pin structured to position the support relative to the diffuser.

14. The apparatus of claim 9 , wherein the support includes a support spool arm.

15. The apparatus of claim 8 , which further includes a passageway formed in the support and structured to slidingly receive the mount stake.

16. A method comprising:
spacing an inner liner of a gas turbine engine combustor from an outer liner, the inner liner having a through passage and the outer liner having a through passage;
installing a mount stake that is elongate between the inner liner and the outer liner of a gas turbine engine combustor such that an outer end of the mount stake extends past the through passage of the outer liner and an inner end of the mount stake extends past the through passage of the inner liner, wherein the mount stake fails to contact a gas turbine engine casing located near the outer liner of the gas turbine engine,
wherein the mount stake is radially oriented between the inner liner and outer liner and includes a radial length larger than a cross sectional dimension taken along the length of the mount stake, wherein the mount stake is structured to retain a spaced relation of the inner liner and the outer liner;
forming a flow space between the mount stake and a neighboring mount stake such that a bulk flow of working fluid is permitted to pass; and
coupling an intermediate portion of the mount stake to a structure of the gas turbine engine at a point upstream of the mount stake
further including a support assembly coupled to the structure of the gas turbine engine, and wherein the support assembly is directly coupled to the mount stake.

17. The method of claim 16 , which further includes axially positioning the mount stake relative to the structure of the gas turbine engine with an alignment device.

18. The method of claim 16 , wherein the support assembly is slidingly coupled to the mount stake.

19. The method of claim 16 , wherein the coupling further includes engaging the support assembly to a gas turbine engine diffuser.

Assignees

• Rice Edward Claude
• Rolls Royce Corp

Inventors

• Rice Edward Claude

Classifications

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title