Gas turbine engine components and cooling cavities

Patent metadata

Field	Value
Publication number	US-2016178201-A1
Application number	US-201514978044-A
Country	US
Kind code	A1
Filing date	Dec 22, 2015
Priority date	Dec 22, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

The present disclosure relates to gas turbine engine components including cooling cavities. One embodiment is directed to a component including a forward surface, an aft surface, at least one inlet on the forward surface and a cavity between the forward surface and the aft surface. The cavity is configured to receive airflow from at least one inlet to provide cooling flow for the component. The cavity includes a plurality of structures within the cavity. The component also includes at least one exit between the forward surface and the aft surface. The plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit. The component having a cavity may be employed by a combustor of a gas turbine engine.

First claim

What is claimed is:

1 . A gas turbine engine component including a cooling cavity, the component comprising:
a forward surface; an aft surface; at least one inlet on the forward surface, the at least one inlet configured to receive air flow; a cavity between the forward surface and the aft surface, wherein the cavity is configured to receive airflow from the at least one inlet to provide cooling flow for the component and wherein the cavity includes a plurality of structures within the cavity; and at least one exit between the forward surface and the aft surface, the at least one exit configured to allow airflow to exit the cavity, wherein the plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit.

2 . The component of claim 1 , wherein the forward surface is a cold side of a combustor bulkhead, and the aft surface is the hot side of the combustor bulkhead.

3 . The component of claim 1 , wherein the at least one inlet is configured to receive airflow directed to a combustor of a gas turbine engine.

4 . The component of claim 1 , wherein the component is a structure including one or more edges, and wherein the cavity is positioned proximate to an edge of the component.

5 . The component of claim 4 , wherein the at least one exit is a cavity exit, and wherein the at least one exit is positioned along the edge of the component and displaced from the at least one inlet.

6 . The component of claim 1 , wherein the plurality of structures are configured to meter air flow by directing airflow within the cavity based on one or more of structure spacing, structure size, structure shape, and structure pattern.

7 . The component of claim 1 , wherein the plurality of structures maintains cooling effectiveness of airflow by allowing greater flow within a first portion of the cavity and reduced flow in a second portion of the cavity, wherein the second portion of the cavity is associated with the at least one exit of the cavity.

8 . The component of claim 1 , wherein the plurality of structures are configured to provide a cooling efficiency that increases as the airflow traverses the cavity, wherein cooling efficiency is a measure of heat pickup by airflow within the cavity.

9 . The component of claim 1 , wherein component is configured to interface with a second component, and a plurality of structures associated with the exit of the component are offset from a plurality of structures associated with an exit of the second component.

10 . The component of claim 1 , wherein at least a first portion of the plurality of structures are configured to provide higher cooling efficiency and a second portion of the plurality of structures are configured to provide a higher cooling effectiveness.

11 . A combustor of a gas turbine engine comprising:
a combustor shell, wherein the shell is configured to engage bulkhead; and a bulkhead including:
a plurality of bulkhead panels, wherein each bulkhead panel includes
a forward surface;
an aft surface;
at least one inlet on the forward surface, the at least one inlet configured to receive air flow;
a cavity between the forward surface and the aft surface, wherein the cavity is configured to receive airflow from the at least one inlet to provide cooling flow for the component and wherein the cavity includes a plurality of structures within the cavity; and
at least one exit between the forward surface and the aft surface, the at least one exit configured to allow airflow to exit the cavity,
wherein the plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit.

12 . The combustor of claim 11 , wherein the forward surface is a cold side of a bulkhead panel, and the aft surface is the hot side of said bulkhead panel.

13 . The combustor of claim 11 , wherein the at least one inlet is configured to receive airflow directed to a combustor of a gas turbine engine.

14 . The combustor of claim 11 , wherein the component is a structure including one or more edges, and wherein the cavity is positioned proximate to an edge of the component.

15 . The combustor of claim 14 , wherein the at least one exit is a cavity exit, and wherein the at least one exit is positioned along the edge of the component and displaced from the at least one inlet.

16 . The combustor of claim 11 , wherein the plurality of structures are configured to meter air flow by directing airflow within the cavity based on one or more of structure spacing, structure size, structure shape, and structure pattern.

17 . The combustor of claim 11 , wherein the plurality of structures maintains cooling effectiveness of airflow by allowing greater flow within a first portion of the cavity and reduced flow in a second portion of the cavity, wherein the second portion of the cavity is associated with the at least one exit of the cavity.

18 . The combustor of claim 11 , wherein the plurality of structures are configured to provide a cooling efficiency that increases as the airflow traverses the cavity, wherein cooling efficiency is a measure of heat pickup by airflow within the cavity.

19 . The combustor of claim 11 , wherein component is configured to interface with a second component, and a plurality of structures associated with the exit of the component are offset from a plurality of structures associated with an exit of the second component.

20 . The combustor of claim 11 , wherein at least a first portion of the plurality of structures are configured to provide higher cooling efficiency and a second portion of the plurality of structures are configured to provide a higher cooling effectiveness.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Stanislav

Classifications

• F23R3/002 Primary

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

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title