Cover plate for a component of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10458291-B2
Application number	US-201615252874-A
Country	US
Kind code	B2
Filing date	Aug 31, 2016
Priority date	Jul 2, 2012
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a platform having a non-gas path side and a gas path side, and said platform having a leading edge rail and a trailing edge rail extending outwardly from said non-gas path side;
an airfoil extending from said gas path side of said platform;
a cover plate positioned adjacent to said non-gas path side of said platform, said cover plate including a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of said platform and a second plurality of openings that communicate a second portion of said cooling air to a second cooling cavity that is separate from said first cooling cavity, and each of said first cooling cavity and said second cooling cavity include a plurality of augmentation features, and said cover plate is a single cover plate configured to cover both of said first cooling cavity and said second cooling cavity;
said first plurality of openings are impingement holes configured to direct said first portion of said cooling air for impingement cooling said first cooling cavity;
said second plurality of openings are core feed holes configured to direct said second portion of said cooling air for providing metered cooling within said second cooling cavity; and
wherein said second cooling cavity radially extends between said trailing edge rail and said gas path side of the component.

2. The component as recited in claim 1 , wherein said platform is an outer diameter platform.

3. The component as recited in claim 1 , wherein said platform is an inner diameter platform.

4. The component as recited in claim 1 , wherein the component is a turbine vane.

5. The component as recited in claim 1 , wherein said cover plate is received at least partially about an opening of an internal core of said airfoil.

6. The component as recited in claim 5 , wherein:
said core feed holes are configured to communicate said second portion of said cooling air radially through said second plurality of openings, then axially within said second cooling cavity in a direction toward said trailing edge rail, and then circumferentially within said second cooling cavity.

7. The component as recited in claim 6 , wherein each of said core feed holes is oriented such that a portion of said second portion of said cooling air communicated by said core feed holes does not impingement cool any surfaces of said second cooling cavity.

8. The component as recited in claim 6 , wherein said second cooling cavity is arranged such that said second portion of said cooling air is communicated in at least two circumferential directions.

9. The component as recited in claim 1 , wherein said second plurality of openings are positioned adjacent said trailing edge rail of said platform.

10. The component as recited in claim 1 , wherein said cover plate is configured to communicate a third portion of said cooling air directly into an internal core of said airfoil.

11. The component as recited in claim 1 , wherein said second plurality of openings are configured in a triangular shaped pattern.

12. The component as recited in claim 1 , wherein said core feed holes are configured to communicate said second portion of said cooling air radially through said second plurality of openings, and then axially within said second cooling cavity, and then circumferentially within said second cooling cavity.

13. The component as recited in claim 12 , wherein said cover plate is received between and abuts against said leading edge rail and said trailing edge rail.

14. A component for a gas turbine engine comprising:
a platform having a non-gas path side and a gas path side;
an airfoil extending from said gas path side of said platform;
a cover plate positioned adjacent to said non-gas path side of said platform, said cover plate including a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of said platform and a second plurality of openings that communicate a second portion of said cooling air to a second cooling cavity that is separate from said first cooling cavity, and each of said first cooling cavity and said second cooling cavity include a plurality of augmentation features, and said cover plate is a single cover plate configured to cover both of said first cooling cavity and said second cooling cavity;
said first plurality of openings are impingement holes configured to direct said first portion of said cooling air for impingement cooling said first cooling cavity;
said second plurality of openings are core feed holes configured to direct said second portion of said cooling air for providing metered cooling within said second cooling cavity; and
wherein said core feed holes are configured to communicate said second portion of said cooling air radially through said second plurality of openings, and then axially within said second cooling cavity, and then circumferentially within said second cooling cavity.

15. The component as recited in claim 14 , wherein said platform includes a wall portion that extends radially away from said non-gas path side to abut against said cover plate and separate said first and second cooling cavities.

16. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication with said combustor section;
wherein one of said compressor section and said turbine section includes at least one component, said at least one component including a platform and an airfoil extending from said platform, wherein said platform includes a non-gas path side and a gas path side and a cover plate positioned at said non-gas path side, said platform having a leading edge rail and a trailing edge rail extending outwardly from said non-gas path side, wherein said cover plate includes a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of said platform and a second plurality of openings that communicate a second portion of said cooling air to a second cooling cavity of said platform that is separate from said first cooling cavity, and each of said first cooling cavity and said second cooling cavity include a plurality of augmentation features, said cover plate configured as a single cover plate configured to cover both said first cooling cavity and said second cooling cavity;
said first plurality of openings are impingement holes configured to direct said first portion of said cooling air for impingement cooling said first cooling cavity;
said second plurality of openings are core feed holes configured to direct said second portion of said cooling air for providing metered cooling within said second cooling cavity; and
wherein said second cooling cavity radially extends between said trailing edge rail and said gas path side of said at least one component.

17. The gas turbine engine as recited in claim 16 , wherein said second plurality of openings are positioned adjacent to said trailing edge rail of said platform and face a suction side of said airfoil.

18. The gas turbine engine as recited in claim 16 , wherein said second plurality of openings are positioned adjacent to said trailing edge rail of said platform and face a pressure side of said airfoil.

19. The gas turbine engine as recited in claim 16 , wherein said plurality of augmentation features include at least one of pin fins and chevron trip strips.

20. The gas turbine engine

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Bergman Russell J

Classifications

• F05D2250/11

  triangular · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/582

  specially adapted for elastic fluid pumps · CPC title

• F01D5/187

  Convection cooling · CPC title

• F05D2240/81

  Cooled platforms · CPC title