Gas turbine engine component with discharge slot having oval geometry

Patent metadata

Field	Value
Publication number	US-10107107-B2
Application number	US-201213598988-A
Country	US
Kind code	B2
Filing date	Aug 30, 2012
Priority date	Jun 28, 2012
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a body portion that extends between a leading edge and a trailing edge, wherein at least one of said leading edge and said trailing edge includes at least one discharge slot having a first portion that includes an oval geometry and a second portion having a different geometry than said first portion.

2. The component as recited in claim 1 , wherein said component is one of a vane and a blade.

3. The component as recited in claim 1 , wherein said at least one discharge slot is disposed at said trailing edge of said body portion.

4. The component as recited in claim 1 , wherein said at least one discharge slot is disposed at said leading edge of said body portion.

5. The component as recited in claim 1 , comprising another discharge slot disposed through at least one of a suction side and a pressure side of said body portion.

6. The component as recited in claim 1 , wherein said first portion of said at least one discharge slot is elliptical shaped.

7. The component as recited in claim 1 , wherein said second portion includes a racetrack shape.

8. The component as recited in claim 7 , wherein said at least one discharge slot includes a shape that is a union between said racetrack shape and said oval geometry.

9. The component as recited in claim 1 , wherein said second portion includes an elliptical shape.

10. The component as recited in claim 9 , wherein said at least one discharge slot includes a shape that is a union between said elliptical shape and said oval geometry.

11. The component as recited in claim 1 , wherein said first portion of said at least one discharge slot is positioned at a position that is one of immediately adjacent to a platform of said component and on said platform.

12. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section along a core flow path;
a turbine section in fluid communication with said combustor section along said core flow path;
a component that extends into said core flow path within at least one of said compressor section and said turbine section, wherein said component includes a body portion that extends between a leading edge and a trailing edge; and
wherein at least one of said leading edge and said trailing edge includes at least one discharge slot having a first portion that includes an oval geometry and a second portion having a different geometry than said first portion.

13. The gas turbine engine as recited in claim 12 , wherein said second portion includes a racetrack shape.

14. The gas turbine engine as recited in claim 13 , wherein said at least one discharge slot includes a shape that is a union between said racetrack shape and said oval geometry.

15. The gas turbine engine as recited in claim 12 , wherein said second portion includes an elliptical shape.

16. The gas turbine engine as recited in claim 15 , wherein said at least one discharge slot includes a shape that is a union between said elliptical shape and said oval geometry.

17. The gas turbine engine as recited in claim 12 , comprising a second discharge slot adjacent to said at least one discharge slot, wherein said second discharge slot is shaped differently from said at least one discharge slot.

18. The gas turbine engine as recited in claim 12 , wherein said first portion of said at least one discharge slot is positioned immediately adjacent to a platform of said component.

19. The gas turbine engine as recited in claim 18 , wherein said first portion of said at least one discharge slot is positioned at a fillet that connects said body portion to said platform.

20. The component as recited in claim 1 , wherein said first portion extends across a first radial distance of said at least one discharge slot and said second portion extends across a second radial distance of said at least one discharge slot.

21. The gas turbine engine as recited in claim 12 , wherein said oval geometry is elliptical shaped.

22. A component for a gas turbine engine, comprising:
a platform;
a body portion that extends from said platform and extends between a leading edge and a trailing edge;
a first discharge slot formed in at least one of said leading edge and said trailing edge, said first discharge slot including a first portion that includes an oval geometry, said first portion positioned at a fillet that connects said body portion to said platform; and
a second discharge slot adjacent to said first discharge slot and shaped differently from said first discharge slot.

Assignees

• Boeke Mark A
• Otero Edwin
• Degray Jeffrey J
• Propheter Hinckley Tracy A
• Fernandez Guillermo J
• Riley Sarah
• United Technologies Corp

Inventors

• Boeke Mark A
• Otero Edwin
• Degray Jeffrey J
• Propheter-Hinckley Tracy A
• Fernandez Guillermo J
• Riley Sarah

Classifications

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title