Combustor configurations for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016290642-A1
Application number	US-201514673629-A
Country	US
Kind code	A1
Filing date	Mar 30, 2015
Priority date	Mar 30, 2015
Publication date	Oct 6, 2016
Grant date	—

Abstract

The present disclosure relates to combustor configurations and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. The plurality of panels include a first panel having a leading and trailing edge, and a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.

First claim

What is claimed is:

1 . A combustor for a gas turbine engine, the combustor comprising:
a support structure; and a plurality of panels mounted to the structure, the plurality of panels defining a combustion cavity of the combustor, wherein the plurality of panels include
a first panel having a leading and trailing edge, and
a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.

2 . The combustor of claim 1 , wherein the support structure is an annular structure including an inner diameter structure and outer diameter structure, and wherein the plurality of panels are mounted to at least one of the inner diameter structure and outer diameter structure.

3 . The combustor of claim 1 , wherein the plurality of panels are heat shield panels.

4 . The combustor of claim 1 , wherein an air gap between the trailing edge of the first panel and the leading edge of the second panel forms at least a portion of a circumferential air gap for the combustor.

5 . The combustor of claim 1 , wherein the trailing edge of the first panel extends beyond the leading edge of the second panel to provide an air flow gap between the first and second panels and wherein portion of the first panel associated with the leading edge is configured to prevent a gas path flow within the combustor to enter the air flow gap.

6 . The combustor of claim 1 , wherein the first panel extends over the second panel along the entire length of the first panel by an amount within the range of 0.5 cm to 2 cm.

7 . The combustor of claim 1 , wherein the second panel includes effusion holes positioned along the leading edge of the second panel.

8 . The combustor of claim 1 , wherein leading edge of the second panel is chamfered.

9 . The combustor of claim 1 , wherein leading edge of the second panel includes one or more features to provide airflow when the trailing edge of the first panel contacts the leading edge of the second panel.

10 . The combustor of claim 9 , wherein the one or more features include groves in the leading edge of the second panel to provide said airflow.

11 . A gas turbine engine comprising:
a combustor having a support structure; and a plurality of panels mounted to the support structure, the plurality of panels defining a combustion cavity of the combustor, wherein the plurality of panels include
a first panel having a leading and trailing edge, and
a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.

12 . The gas turbine engine of claim 10 , wherein the support structure is an annular structure including an inner diameter structure and outer diameter structure, and wherein the plurality of panels are mounted to at least one of the inner diameter structure and outer diameter structure.

13 . The gas turbine engine of claim 10 , wherein the plurality of panels are heat shield panels.

14 . The gas turbine engine of claim 10 , wherein an air gap between the trailing edge of the first panel and the leading edge of the second panel forms at least a portion of a circumferential air gap for the combustor.

15 . The gas turbine engine of claim 10 , wherein the trailing edge of the first panel extends beyond the leading edge of the second panel to provide an air flow gap between the first and second panels and wherein portion of the first panel associated with the leading edge is configured to prevent a gas path flow within the combustor to enter the air flow gap.

16 . The gas turbine engine of claim 10 , wherein the first panel extends over the second panel along the entire length of the first panel by an amount within the range of 0.5 cm to 2 cm.

17 . The gas turbine engine of claim 10 , wherein the second panel includes effusion holes positioned along the leading edge of the second panel.

18 . The gas turbine engine of claim 10 , wherein leading edge of the second panel is chamfered.

19 . The gas turbine engine of claim 10 , wherein leading edge of the second panel includes one or more features to provide airflow when the trailing edge of the first panel contacts the leading edge of the second panel.

20 . The gas turbine engine of claim 19 , wherein the one or more features include groves in the leading edge of the second panel to provide said airflow.

Assignees

• United Technologies Corp

Inventors

• Kwoka David
• Rezvani Reza
• Eastwood Jonathan Jeffery

Classifications

• F23R3/44

  Combustion chambers comprising a {single} tubular flame tube within a tubular casing (reverse-flow combustion chambers F23R3/54) · CPC title

• F23R3/002 Primary

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

• F23R3/08

  between annular flame tube sections, e.g. flame tubes with telescopic sections · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title