Combustor aft mount assembly

Patent metadata

Field	Value
Publication number	US-10066837-B2
Application number	US-201514627029-A
Country	US
Kind code	B2
Filing date	Feb 20, 2015
Priority date	Feb 20, 2015
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.

First claim

We claim:

1. A gas turbine engine, comprising:
a compressor discharge casing;
a plurality of combustors configured in an annular array; and
a plurality of aft mounting assemblies;
wherein an aft mounting assembly of the plurality of aft mounting assemblies mounts a combustor of the plurality of combustors to an inner diameter of the compressor discharge casing;
wherein the aft mounting assembly comprises an aft frame attached to the combustor, a mounting flange attached to an inner portion of the aft frame, and a mounting bracket attached to the compressor discharge casing and pivotally attached to the mounting flange;
wherein the mounting bracket comprises a mounting bracket base with a pair of bolting wings extending circumferentially therefrom around the compressor discharge casing and perpendicular to a flow of combustion gases and the pair of bolting wings extend to opposite circumferential sides of the aft frame.

2. The gas turbine engine of claim 1 , wherein the combustor comprises a liner and wherein the aft frame is connected to the liner.

3. The gas turbine engine of claim 2 , wherein the aft frame is mounted on the mounting bracket.

4. The gas turbine engine of claim 1 , wherein the pair of bolting wings comprise a bolt flange, a bolt aperture, and a mounting bolt extending in the bolt aperture.

5. The gas turbine engine of claim 1 , wherein the mounting bracket comprises an inner diameter mounting bracket.

6. The gas turbine engine of claim 1 , wherein the mounting bracket base comprises a plurality of base flanges.

7. The gas turbine engine of claim 6 , wherein the plurality of base flanges comprises a base flange aperture.

8. The gas turbine engine of claim 1 , wherein the mounting flange is pivotally attached to the mounting bracket via a pivot rod assembly.

9. The gas turbine engine of claim 8 , wherein the pivot rod assembly comprises a pivot rod and a pivot rod flange.

10. The gas turbine engine of claim 9 , wherein the mounting bracket base comprises at least one base flange extending therefrom, wherein the at least one base flange comprises a flange aperture.

11. The gas turbine engine of claim 10 , wherein the pivot rod passes through the flange aperture and the pivot rod flange to pivotally attach the mounting flange to the mounting bracket.

12. A method of securing a mounting assembly of a combustor to a compressor discharge casing, comprising:
positioning a mounting bracket on an inner diameter of the compressor discharge casing;
attaching an aft frame to the combustor;
wherein the mounting bracket comprises a mounting bracket base with a pair of bolting wings extending circumferentially therefrom around the compressor discharge casing and perpendicular to a flow of combustion gases and the pair of bolting wings extend to opposite circumferential sides of the aft frame;
pivotally attaching the mounting bracket to the aft frame via a mounting flange attached to an inner portion of the aft frame;
accessing the bolting wings positioned circumferentially adjacent to the combustor from either inside the compressor discharge casing or from openings in a turbine shell; and
securing a bolt through the bolting wing and the compressor discharge casing in a radial direction.

13. The method of claim 12 , further comprising the step of accessing the bolting wing from radially outside the combustor.

Assignees

• Gen Electric

Inventors

• Dicintio Richard Martin
• Monaghan Elizabeth Angelyn

Classifications

• F02C5/02 Primary

  characterised by the arrangement of the combustion chamber in the chamber in the plant (combustion chambers per se F23R) · CPC title

• F01D25/28

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

• F02C3/14

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title