Turbine engine combustor heat shield with multi-angled cooling apertures

Patent metadata

Field	Value
Publication number	US-2016265773-A1
Application number	US-201415032119-A
Country	US
Kind code	A1
Filing date	Nov 4, 2014
Priority date	Nov 4, 2013
Publication date	Sep 15, 2016
Grant date	—

Abstract

A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

First claim

What is claimed is:

1 . A combustor for a turbine engine, the combustor comprising:
a combustor wall including a shell and a heat shield attached to the shell; wherein one or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield; and wherein the apertures in the heat shield include a first aperture and a second aperture, and an angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

2 . The combustor of claim 1 , wherein
the one or more cooling cavities include a first cavity and a second cavity; the first aperture is fluidly coupled with the first cavity; and the second aperture is fluidly coupled with the second cavity.

3 . The combustor of claim 2 , wherein an angle of incidence between each of the apertures in the heat shield that are fluidly coupled with the first cavity and the surface is substantially equal to the angle of incidence between the first aperture and the surface.

4 . The combustor of claim 2 , wherein the combustor wall further includes a rail arranged between the first cavity and the second cavity.

5 . The combustor of claim 1 , wherein
the one or more cooling cavities include a first cavity; and the first aperture and the second aperture are fluidly coupled with the first cavity.

6 . The combustor of claim 1 , wherein
the heat shield includes a plurality of panels; and a first of the panels includes the first aperture and the second aperture.

7 . The combustor of claim 6 , wherein
the first of the panels extends between an upstream end and a downstream end; the second aperture is located at the downstream end; and the angle of incidence of the second aperture is greater than the angle of incidence of the first aperture.

8 . The combustor of claim 1 , wherein
the heat shield includes a plurality of panels; a first of the panels includes the first aperture; and a second of the panels includes the second aperture.

9 . The combustor of claim 1 , where a diameter of the first aperture at the surface is substantially equal to a diameter of the second aperture at the surface.

10 . The combustor of claim 1 , wherein a diameter of the first aperture at the surface is different than a diameter of the second aperture at the surface.

11 . The combustor of claim 1 , wherein a diameter of the first aperture increases as the first aperture extends through the heat shield away from the shell.

12 . The combustor of claim 1 , wherein
the first aperture is one of a plurality of first apertures defined in the heat shield; a density of the first apertures in a first region of the heat shield is different than a density of the first apertures in a second region of the heat shield.

13 . The combustor of claim 12 , wherein the density of the first apertures in the first region and the density of the first apertures in the second region are selected to provide more cooling to first region than the second region.

14 . A combustor for a turbine engine, the combustor comprising:
a combustor wall including a shell and a heat shield attached to the shell; the heat shield defining a plurality of effusion apertures that includes a first aperture and a second aperture; wherein the first aperture extends along a centerline that is offset from a surface of the heat shield by a first angle, and the second aperture extends along a centerline that is offset from the surface by a second angle that is different than the first angle.

15 . The combustor of claim 14 , wherein
a plurality of cooling cavities are defined between the shell and the heat shield; the first aperture is fluidly coupled with a first of the cooling cavities; and the second aperture is fluidly coupled with a second of the cooling cavities.

16 . A combustor for a turbine engine, the combustor comprising:
a combustor shell; and a combustor heat shield attached to the shell; wherein one or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield; and wherein the apertures in the heat shield include a first aperture and a second aperture, and an angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

17 . The combustor of claim 16 , wherein
the one or more cooling cavities include a first cavity and a second cavity; the first aperture is fluidly coupled with the first cavity; and the second aperture is fluidly coupled with the second cavity.

18 . The combustor of claim 16 , wherein
the one or more cooling cavities include a first cavity; and the first aperture and the second aperture are fluidly coupled with the first cavity.

19 . The combustor of claim 16 , wherein
the heat shield includes a plurality of panels; and a first of the panels includes the first aperture and the second aperture.

20 . The combustor of claim 16 , further comprising:
a combustor first wall; a combustor second wall including the shell and the heat shield; and a combustor bulkhead extending between the first wall and the second wall; wherein the first wall, the second wall and the bulkhead form a combustion chamber.

Assignees

• United Technologies Corp

Inventors

• Moura Dennis M
• Pacheco-Tougas Monica
• Eastwood Jonathan J
• Bouldin Lee E

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/002 Primary

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

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/202

  by film cooling · CPC title