Nozzle guide for a combustor of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016146465-A1
Application number	US-201514950876-A
Country	US
Kind code	A1
Filing date	Nov 24, 2015
Priority date	Nov 25, 2014
Publication date	May 26, 2016
Grant date	—

Abstract

A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

First claim

What is claimed is:

1 . A nozzle guide for a combustor of a gas turbine engine, the nozzle guide comprising:
an annular structure having an inner surface and outer surface, the inner surface including a plurality of cooling holes, wherein the cooling holes of the annular structure are configured to receive air flow; a guide plate configured to engage with a combustor shell, the guide plate including a plurality of openings located proximate to an outer periphery of the guide plate, wherein the plurality of openings provide air flow to the outer periphery of the guide plate; and a plurality of cooling passages within the inner and outer surface of the annular structure and within the guide plate, the plurality of cooling passages configured to provide air flow from the plurality of cooling holes to the plurality of openings of the guide plate.

2 . The nozzle guide of claim 1 , wherein the annular structure is configured to receive a fuel nozzle.

3 . The nozzle guide of claim 1 , wherein the guide plate engages with a combustor shell to contact a combustor shell bulkhead.

4 . The nozzle guide of claim 1 , wherein a distal end of the guide plate is angled towards a combustor shell bulkhead.

5 . The nozzle guide of claim 1 , wherein a thickness of the guide plate is increased for mounting the nozzle guide to a combustor shell.

6 . The nozzle guide of claim 1 , wherein the openings are holes along the mounting surface of the guide plate in close proximity to the outer periphery of the guide plate.

7 . The nozzle guide of claim 1 , wherein the openings are wavelike deformations in a surface of the guide plate.

8 . The nozzle guide of claim 1 , wherein the openings provide radial air flow to cool the guide plate surface.

9 . The nozzle guide of claim 1 , wherein the nozzle guide is a diffuser for a combustor shell.

10 . A combustor of a gas turbine engine comprising:
a combustor shell, wherein the shell is configured to receive a nozzle guide; and a nozzle guide including:
an annular structure having an inner surface and outer surface, the inner surface including a plurality of cooling holes, wherein the cooling holes of the annular structure are configured to receive air flow;
a guide plate configured to engage with a combustor shell, the guide plate including a plurality of openings located proximate to an outer periphery of the guide plate, wherein the plurality of openings provide air flow to the outer periphery of the guide plate; and
a plurality of cooling passages within the inner and outer surface of the annular structure and within the guide plate to provide air flow from the plurality of cooling holes to the plurality of openings of the guide plate.

11 . The nozzle guide of claim 10 , wherein the annular structure is configured to receive a fuel nozzle.

12 . The nozzle guide of claim 10 , wherein the guide plate engages with a combustor shell to contact a combustor shell bulkhead.

13 . The nozzle guide of claim 10 , wherein a distal end of the guide plate is angled towards a combustor shell bulkhead.

14 . The nozzle guide of claim 10 , wherein a thickness of the distal end of the guide plate flange is increased for mounting the nozzle guide to the combustor shell.

15 . The nozzle guide of claim 10 , wherein the openings are holes along the mounting surface of the guide plate in close proximity to the outer periphery of the guide plate.

16 . The nozzle guide of claim 10 , wherein the openings are wavelike deformations in a surface of the guide plate.

17 . The nozzle guide of claim 10 , wherein the openings provide radial air flow to cool the guide plate surface.

18 . The nozzle guide of claim 10 , wherein the nozzle guide is a diffuser for a combustor shell.

19 . A nozzle guide for a combustor of a gas turbine engine, the nozzle guide comprising:
an annular structure having an inner surface and outer surface, the inner surface including a plurality of cooling holes, wherein the cooling holes of the annular structure are configured to receive air flow; a guide plate extending from a base of the annular structure, the guide plate including a plurality of openings located proximate to an outer periphery of the guide plate, wherein the plurality of openings provide air flow to the outer periphery of the guide plate, and wherein the outer periphery extends away from the base of the annular structure; and a plurality of cooling passages within the inner and outer surface of the annular structure and within the guide plate to provide air flow from the plurality of cooling holes to the plurality of openings of the guide plate.

20 . The nozzle guide of claim 19 , wherein the outer periphery of the guide plate is curved to extend into a combustor shell away from the annular structure.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Stanislav

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/10 Primary

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title