Film cooling channel array having anti-vortex properties

Patent metadata

Field	Value
Publication number	US-9316104-B2
Application number	US-201213660148-A
Country	US
Kind code	B2
Filing date	Oct 25, 2012
Priority date	Oct 25, 2012
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A cooling channel array carried by a component wall of a gas turbine engine is provided. The cooling channel array comprises a diffusion cavity and a metering section. The metering section comprises a main hole and two or more side holes. The side holes may be separate from the main hole or may branch off of the main hole. The diffusion cavity may incorporate a lobed configuration to help diffuse cooling fluid as it exits the cooling channel array.

First claim

What is claimed is:

1. A cooling channel array carried by a component wall of a gas turbine engine having a first surface and a second surface, the cooling channel array comprising:
a diffusion cavity defined by a face carried by the component wall and having an outlet on the second surface, the diffusion cavity having two or more lobes, each lobe partly defined by a raised, contoured section on the face and each lobe defining a lobe axis diverging from a central axis of the diffusion cavity; and
a metering section comprising a main hole and two or more side holes, the main hole having an inlet on the first surface and an outlet located on the face of the diffusion cavity, each side hole having an inlet and having an outlet located on the lobe axis of the face of the diffusion cavity.

2. The cooling channel array claim 1 wherein:
at least one of the side hole inlets is located on the first surface.

3. The cooling channel array of claim 2 wherein:
all of the side hole inlets are located on the first surface.

4. The cooling channel array of claim 2 wherein the number of side holes is two.

5. The cooling channel array of claim 2 wherein:
the main hole and the side holes each have a constant flow cross-sectional area.

6. The cooling channel array of claim 2 wherein:
the main hole and the side holes each have a diameter; and
the diameters of the side holes are smaller than the diameter of the main hole.

7. The cooling channel array of claim 2 wherein:
the side hole outlets are laterally aligned with the main hole outlet.

8. The cooling channel array of claim 2 wherein:
the side hole outlets are laterally upstream or downstream of the main hole outlet.

9. The cooling channel array of claim 2 wherein:
the side holes diverge from the main hole.

10. The cooling channel array of claim 2 wherein:
the diffusion cavity has the central axis aligned with the main hole outlet, a side hole outlet located on a first lobe axis defined by a first lobe, and another side hole outlet located on a second lobe axis defined by a second lobe.

11. The cooling channel array of claim 1 wherein:
at least one of the side holes branches off of the main hole.

12. The cooling channel array of claim 11 wherein:
every side hole branches off of the main hole.

13. The cooling channel array of claim 11 wherein the number of side holes is two.

14. The cooling channel array of claim 11 wherein:
the main hole and the side holes each have a constant flow cross-sectional area.

15. The cooling channel array of claim 11 wherein:
the main hole and the side holes each have a diameter; and
the diameters of the side holes are smaller than the diameter of the main hole.

16. The cooling channel array of claim 11 wherein:
the side hole outlets are laterally aligned with the main hole outlet.

17. The cooling channel array of claim 11 wherein:
the side hole outlets are laterally upstream or downstream of the main hole outlet.

18. The cooling channel array of claim 11 wherein:
the diffusion cavity has the central axis aligned with the main hole, a side hole aligned with a first lobe axis defined by a first lobe, and another side hole aligned with a second lobe axis defined by a second lobe.

19. The cooling channel array of claim 1 wherein the component wall is part of a turbine blade.

20. The cooling channel array of claim 1 wherein the component wall is part of a turbine vane.

Assignees

• United Technologies Corp

Inventors

• Xu Jinquan

Classifications

• F05D2240/81

  Cooled platforms · CPC title

• F23R3/002

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

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title