Common joint for a combustor, diffuser, and tobi of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016017755-A1
Application number	US-201314759700-A
Country	US
Kind code	A1
Filing date	Jan 29, 2013
Priority date	Jan 29, 2013
Publication date	Jan 21, 2016
Grant date	—

Abstract

An assembly for a gas turbine engine is disclosed. The gas turbine engine may have a combustor, a diffuser, and a tangential onboard injector. The assembly may include a common joint between the combustor, the diffuser, and the tangential onboard injector.

First claim

What is claimed is:

1 . An assembly for a gas turbine engine, comprising:
a combustor; a diffuser surrounding the combustor; a tangential onboard injector downstream of the diffuser; and a common joint joining the combustor, the diffuser, and the tangential onboard injector.

2 . The assembly of claim 1 , wherein the joint couples a flange of the tangential onboard injector to a combustor flange of the combustor, and wherein the joint further couples the flange of the tangential onboard injector and the combustor flange to a flange of the diffuser.

3 . The assembly of claim 2 , wherein the combustor flange extends from a structural support of the combustor, the structural support having openings and extending from the combustor flange to an inner liner of the combustor.

4 . The assembly of claim 3 , wherein a size of the openings is determined by a desired amount of flow into the tangential onboard injector.

5 . The assembly of claim 3 , wherein the joint and the structural support provide mounting support for the combustor.

6 . The assembly of claim 3 , wherein the structural support provides flexibility for an interference fit between the combustor and a turbine of the gas turbine engine.

7 . The assembly of claim 3 , wherein the structural support provides for tolerance differences between the combustor and the turbine.

8 . The assembly of claim 1 , wherein the joint includes a lip to radially locate at least one of the combustor, the diffuser, and tangential onboard injector.

9 . The assembly of claim 1 , wherein the common joint assists in locating the tangential onboard injector, combustor, and diffuser within the gas turbine engine.

10 . The assembly of claim 1 , wherein the combustor, diffuser, and tangential onboard injector are coupled together at the joint by a plurality of nuts and bolts, and wherein the plurality of nuts and bolts hold the combustor, diffuser, and tangential onboard injector in position.

11 . A gas turbine engine, comprising:
a compressor; a combustor downstream of the compressor; a turbine downstream of the combustor; a diffuser surrounding the combustor; a tangential onboard injector downstream of the combustor; and a single joint coupling the combustor, the diffuser, and the tangential onboard injector.

12 . The gas turbine engine of claim 11 , wherein the single joint couples a flange of the tangential onboard injector to a structural support of the combustor and to a case of the diffuser.

13 . The gas turbine engine of claim 12 , wherein the diffuser case includes a diffuser flange and the combustor structural support includes a combustor flange, and wherein the combustor flange is fit in-between the diffuser flange and the flange of the tangential onboard injector.

14 . The gas turbine engine of claim 13 , wherein the structural support of the combustor supports the combustor within the gas turbine engine, the structural support comprising a wall extending from the combustor flange to an inner liner of the combustor, the wall having a plurality of openings defining a flow passage to an inlet of the tangential onboard injector, and wherein a size of the openings is determined by a desired amount of flow into the tangential onboard injector.

15 . The gas turbine engine of claim 14 , wherein the structural support provides flexibility for an interference fit between the combustor and the turbine.

16 . The gas turbine engine of claim 13 , wherein the single joint assists in locating the combustor, diffuser, and tangential onboard injector within the gas turbine engine.

17 . An assembly for a gas turbine engine having a combustor, a diffuser surrounding the combustor, and a tangential onboard injector, the assembly comprising:
at least one common joint between the combustor, the diffuser, and the tangential onboard injector.

18 . The assembly of claim 17 , wherein the at least one common joint couples a flange of the diffuser to a flange of the combustor to a flange of the tangential onboard injector.

19 . The assembly of claim 18 , further comprising a plurality of fasteners for assembling the at least one common joint together.

20 . The assembly of claim 19 , wherein the at least one common joint assists in locating the combustor, diffuser, and tangential onboard injector within the gas turbine engine.

Assignees

• United Technologies Corp

Inventors

• Low Kevin Joseph

Classifications

• F05D2240/90

  Mounting on supporting structures or systems · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D25/28 Primary

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