Turbine engine multi-walled structure with internal cooling element(s)

Patent metadata

Field	Value
Publication number	US-10753608-B2
Application number	US-201415034717-A
Country	US
Kind code	B2
Filing date	Nov 21, 2014
Priority date	Nov 21, 2013
Publication date	Aug 25, 2020
Grant date	Aug 25, 2020

Abstract

A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

First claim

What is claimed is:

1. A structure for a turbine engine, the structure comprising:
a shell including a first surface; and
a heat shield including a rail, a textured second surface, a textured third surface, a plurality of first cooling elements and a plurality of second cooling elements, the texture of a first portion of the second surface different than the texture of a first portion of the third surface, the first cooling elements partially defining the second surface, the second cooling elements partially defining the third surface, and a first of the first cooling elements having a different geometric configuration than a first of the second cooling elements;
wherein the first surface and the second surface define a first cooling cavity between the shell and the heat shield, and the first surface and the third surface define a second cooling cavity between the shell and the heat shield;
wherein each cooling cavity tapers in height as the respective cooling cavity extends away from the rail;
wherein the rail fluidly isolates the first cooling cavity from the second cooling cavity.

2. The structure of claim 1 , wherein the heat shield defines
first cooling apertures at the first portion of the second surface with the first cooling apertures fluidly coupled with the first cooling cavity; and
second cooling apertures at the first portion of the third surface with the second cooling apertures fluidly coupled with the second cooling cavity.

3. The structure of claim 2 , wherein the rail is between the second surface and the third surface, and the texture of a second portion of the second surface at the rail is substantially the same as the texture of a second portion of the third surface at the rail.

4. The structure of claim 1 , wherein a density of the first cooling elements is different than a density of the second cooling elements.

5. The structure of claim 1 , wherein
the first of the first cooling elements comprises a point protrusion; and
the first of the second cooling elements comprises a rib.

6. The structure of claim 5 , wherein the point protrusion is configured as a nodule or a pin.

7. The structure of claim 5 , wherein at least a portion of the rib is configured as a chevron.

8. The structure of claim 5 , wherein the heat shield defines first cooling apertures fluidly coupled with the first cooling cavity and second cooling apertures fluidly coupled with the second cooling cavity, the point protrusion is disposed next to one of the first cooling apertures, and the rib is disposed next to one or more of the second cooling apertures.

9. The structure of claim 8 , wherein
the heat shield includes first and second end rails;
the heat shield defines the first cooling apertures at the first end rail; and
the heat shield defines the second cooling apertures at the second end rail.

10. The structure of claim 9 , wherein at least one of
the first cooling cavity is configured to direct substantially all first cavity air which enters the first cooling cavity through the first cooling apertures; or
the second cooling cavity is configured to direct substantially all second cavity air which enters the second cooling cavity through the second cooling apertures.

11. The structure of claim 1 , wherein the heat shield includes a plurality of heat shield panels, and one of the plurality of heat shield panels includes the second surface and the third surface.

12. The structure of claim 1 , wherein
the first surface and the second surface converge towards one another, and
the first surface and the third surface converge towards one another.

13. The structure of claim 1 , wherein
the first cooling cavity fluidly couples a plurality of shell cooling apertures defined in the shell with a plurality of heat shield cooling apertures defined in the heat shield at a second rail, and
the heat shield is configured such that substantially all air within the first cooling cavity is directed through the heat shield cooling apertures defined in the heat shield at the second rail.

14. The structure of claim 1 , wherein
the heat shield includes a base that at least partially defines the second surface and the third surface, and
a first portion of the base is thicker than a second portion of the base.

15. A structure for a turbine engine, the structure comprising:
a shell and a heat shield with first and second cooling cavities between the shell and the heat shield, the first cooling cavity fluidly isolated from the second cooling cavity by a rail within the structure;
wherein the heat shield includes a plurality of first cooling elements and a plurality of second cooling elements, the first cooling elements extend partially into the first cooling cavity, one of the first cooling elements comprises a point protrusion, the second cooling elements extend partially into the second cooling cavity, and one of the second cooling elements comprises a rib;
wherein each cooling cavity tapers in height as the respective cooling cavity extends away from the rail.

16. The structure of claim 15 , wherein the first cooling cavity or the second cooling cavity is defined vertically between a surface of the shell and a surface of the heat shield that converge towards one another.

17. The structure of claim 15 , wherein the heat shield defines cooling apertures at the rail fluidly coupled with one of the first cooling cavity and the second cooling cavity, and configured to outwardly direct substantially all air entering the one cooling cavity through the cooling apertures.

18. The structure of claim 15 , wherein
the heat shield includes a base that at least partially defines the first and the second cooling cavities and
a first portion of the base is thicker than a second portion of the base.

19. The structure of claim 1 , wherein
the first of the second cooling elements is configured as a rib comprising a plurality of chevrons; and
a first of the chevrons is directedly connected to and contiguous with, in an end-to-end fashion, a second of the chevrons and a third of the chevrons.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Cunha Frank J
• Kostka Jr Stanislav

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F23M5/00

  Casings; Linings; Walls · CPC title

• F23M5/08

  Cooling thereof; Tube walls · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title