Turbine engine combustor heat shield with multi-angled cooling apertures

Patent metadata

Field	Value
Publication number	US-10215410-B2
Application number	US-201415032119-A
Country	US
Kind code	B2
Filing date	Nov 4, 2014
Priority date	Nov 4, 2013
Publication date	Feb 26, 2019
Grant date	Feb 26, 2019

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;
the heat shield defining a plurality of effusion apertures that includes a first effusion aperture and a second effusion aperture;
wherein the first effusion aperture extends along a centerline that is offset from a surface of the heat shield by a first angle, the first angle being greater than 0° and less than 90°, and the second effusion aperture extends along a centerline that is offset from the surface by a second angle, the second angle being greater than 0° and less than 90°, wherein the second angle is different than the first angle;
wherein the first effusion aperture is one of a plurality of first effusion apertures defined in the heat shield, and a density of the plurality of first effusion apertures in a first region of the heat shield is greater than a density of the plurality of first effusion apertures in a second region of the heat shield, wherein the density of the plurality of first effusion apertures in the second region of the heat shield is greater than zero; and
wherein the second effusion aperture is one of a plurality of second effusion apertures defined in the heat shield, and a density of the plurality of second effusion apertures in the second region of the heat shield is greater than a density of the plurality of second effusion apertures in the first region of the heat shield, wherein the density of the plurality of second effusion apertures in the first region of the heat shield is greater than zero.

2. The combustor of claim 1 , wherein
a plurality of cooling cavities are defined between the shell and the heat shield;
at least one first effusion aperture of the plurality of first effusion apertures is fluidly coupled with a first cooling cavity of the plurality of cooling cavities; and
at least one second effusion aperture of the plurality of second effusion apertures is fluidly coupled with a second cooling cavity of the plurality of cooling cavities.

3. 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 plurality of 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 greater than 0° and less than 90°, an angle of incidence between the second aperture and the surface is greater than 0° and less than 90°, and the angle of incidence between the first aperture and the surface is different than the angle of incidence between the second aperture and the surface;
wherein the first aperture is one of a plurality of first apertures defined in the heat shield, and a density of the plurality of first apertures in a first region of the heat shield is greater than a density of the plurality of first apertures in a second region of the heat shield, wherein the density of the plurality of first apertures in the second region of the heat shield is greater than zero; and
wherein the second aperture is one of a plurality of second apertures defined in the heat shield, and a density of the plurality of second apertures in the first region of the heat shield is less than a density of the plurality of second apertures in the second region of the heat shield, wherein the density of the plurality of second apertures in the first region is greater than zero.

4. The combustor of claim 3 , wherein
the one or more cooling cavities include a first cavity and a second cavity;
at least one first aperture of the plurality of first apertures is fluidly coupled with the first cavity; and
at least one second aperture of the plurality of second apertures is fluidly coupled with the second cavity.

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

6. The combustor of claim 3 , wherein the one or more cooling cavities include a first cavity; and
at least one first aperture of the plurality of first apertures and at least one first aperture of the plurality of second apertures are fluidly coupled with the first cavity.

7. The combustor of claim 3 , wherein the heat shield includes a plurality of panels; and a first panel of the plurality of panels includes the plurality of first apertures and the plurality of second apertures.

8. The combustor of claim 7 , wherein
the first panel of the plurality of panels includes an upstream end and a downstream end;
at least one second aperture of the plurality of second apertures is located at the downstream end; and
the angle of incidence of each second aperture of the plurality of second apertures is greater than the angle of incidence of each first aperture of the plurality of first apertures.

9. The combustor of claim 3 , wherein
the heat shield includes a plurality of panels;
a first panel of the plurality of panels includes at least one first aperture of the plurality of first apertures; and
a second panel of the plurality of panels includes at least one second aperture of the plurality of second apertures.

10. The combustor of claim 3 , wherein a diameter of at least one first aperture of the plurality of first apertures at the surface is substantially equal to a diameter of at least one second aperture of the plurality of second apertures at the surface.

11. The combustor of claim 3 , wherein a diameter of at least one first aperture of the plurality of first apertures at the surface is different than a diameter of at least one second aperture of the plurality of second apertures at the surface.

12. The combustor of claim 3 , wherein a diameter of at least one first aperture of the plurality of first apertures increases as the at least one first aperture extends through the heat shield away from the shell.

13. The combustor of claim 3 , wherein the density of the plurality of first apertures in the first region and the density of the plurality of first apertures in the second region are configured to provide more cooling to the first region than to the second region.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/15

  Heat shield · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title