Film cooled multi-walled structure with one or more indentations

Patent metadata

Field	Value
Publication number	US-2016273771-A1
Application number	US-201415034689-A
Country	US
Kind code	A1
Filing date	Nov 25, 2014
Priority date	Nov 25, 2013
Publication date	Sep 22, 2016
Grant date	—

Abstract

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

First claim

What is claimed is:

1 . An assembly for a turbine engine, the assembly comprising:
a shell and a heat shield with a cooling cavity between the shell and the heat shield, the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity, wherein the cooling apertures are fluidly coupled with the cooling cavity, and wherein the indentation is configured such that cooling air directed from a first of the cooling apertures at least partially circulates against the side of the heat shield.

2 . The assembly of claim 1 , wherein the shell defines a plurality of cooling apertures that are fluidly coupled with the cooling apertures in the heat shield by the cooling cavity.

3 . The assembly of claim 1 , wherein the heat shield includes a first surface and a second surface with the first surface defining an outlet of the first of the cooling apertures and the second surface defining the indentation, and wherein the first and second surfaces are adjacent and contiguous with one another.

4 . The assembly of claim 1 , wherein an outlet of the first of the cooling apertures is separated by a distance from the indentation.

5 . The assembly of claim 1 , wherein an outlet of the first of the cooling apertures intersects the indentation.

6 . The assembly of claim 1 , wherein the first of the cooling apertures is circumferentially aligned with the indentation.

7 . The assembly of claim 1 , wherein the first of the cooling apertures is circumferentially offset from the indentation.

8 . The assembly of claim 1 , further comprising a surface that defines the indentation, wherein the surface has a circular peripheral geometry.

9 . The assembly of claim 1 , further comprising a surface that defines the indentation, wherein the surface has an oval peripheral geometry.

10 . The assembly of claim 1 further comprising a surface that defines the indentation, wherein the surface has a peripheral geometry with one or more concave sections and one or more convex sections.

11 . The assembly of claim 1 , wherein an annular surface of the heat shield defines the indentation.

12 . The assembly of claim 1 , wherein a second of the cooling apertures is configured to direct cooling air away from the cooling cavity, and the indentation is further configured such that cooling air directed from the second cooling aperture at least partially circulates against the side of the heat shield.

13 . The assembly of claim 1 , wherein
the heat shield further defines a second indentation in the side of the heat shield, and the second indentation is configured such that cooling air directed from a second of the cooling apertures at least partially circulates against the side of the heat shield.

14 . The assembly of claim 1 , wherein the heat shield includes an arcuate panel in which the first of the cooling apertures and the indentation are defined.

15 . The assembly of claim 1 , further comprising a tubular combustor wall that includes the shell and the heat shield.

16 . An assembly for a turbine engine, the assembly comprising:
a shell; and a heat shield attached to the shell with a cooling cavity extending between the heat shield and the shell, the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity, wherein the cooling apertures are fluidly coupled with the cooling cavity, and an outlet of a first of the cooling apertures is located at an edge of the indentation.

17 . The assembly of claim 16 , wherein the indentation is configured such that cooling air directed from the outlet at least partially circulates against the side of the heat shield.

18 . The assembly of claim 16 , wherein
the heat shield extends vertically between a chamber surface and a cavity surface that defines a portion of the cooling cavity; a point of an indentation surface that defines the indentation is located a vertical distance from the cavity surface; and the vertical distance is between about fifty percent and about ninety percent of a vertical thickness of the heat shield measured between the cavity and the chamber surfaces.

19 . The assembly of claim 16 , wherein a cross-sectional area of the outlet is between about one percent and about fifty percent of an area of an indentation surface that defines the indentation.

20 . The assembly of claim 16 , wherein the shell defines a plurality of cooling apertures that are fluidly coupled with the cooling apertures in the heat shield by the cooling cavity.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Jr Stanislav

Classifications

• F05D2250/23

  prismatic · 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

• F05D2260/2212

  by creating turbulence · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F05D2250/24

  ellipsoidal · CPC title