Gas turbine engine component having platform trench

Patent metadata

Field	Value
Publication number	US-10364680-B2
Application number	US-201213585274-A
Country	US
Kind code	B2
Filing date	Aug 14, 2012
Priority date	Aug 14, 2012
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face;
a trench disposed on at least one of said first mate face and said second mate face;
a plurality of cooling holes axially disposed within said trench; and
a cavity disposed at least partially inside an airfoil that extends from said platform, said plurality of cooling holes being configured to directly receive fluid from a radially extending portion of said cavity.

2. The component as recited in claim 1 , wherein said platform is part of a blade.

3. The component as recited in claim 1 , wherein said platform is part of a vane.

4. The component as recited in claim 1 , comprising another trench disposed on the other of said first mate face and said second mate face.

5. The component as recited in claim 1 , wherein an outlet of each of said plurality of cooling holes opens into said trench.

6. The component as recited in claim 1 , wherein said trench extends between said leading edge and said trailing edge of said platform.

7. The component as recited in claim 1 , wherein said trench is radially centered on at least one of said first mate face and said second mate face.

8. The component as recited in claim 1 , wherein said trench is disposed on a pressure side of the component.

9. The component as recited in claim 1 , wherein said trench is disposed on a suction side of the component.

10. The component as recited in claim 1 , wherein said trench is disposed on each of a pressure side and a suction side of the component.

11. The component as recited in claim 1 , wherein said cavity extends inside said platform, inside said airfoil and inside a root portion that extends from said platform in an opposite direction from said airfoil.

12. The component as recited in claim 1 , wherein said radially extending portion of said cavity extends through both a root portion and said airfoil of said component.

13. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication said combustor section;
a component positioned within at least one of said compressor section and said turbine section, wherein said component includes:
a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face;
a trench disposed on at least one of said first mate face and said second mate face, said trench extending from an upstream wall disposed proximate to said leading edge to a downstream wall disposed proximate to said trailing edge;
at least one cooling hole disposed within said trench; and
cavity extending inside said platform, said cavity having radially extending portion configured to directly communicate fluid to said at least one cooling hole; and

a second component adjacent to said component, wherein a seal is positioned between said component and said second component.

14. The gas turbine engine as recited in claim 13 , wherein said component is a turbine blade.

15. The gas turbine engine as recited in claim 13 , wherein said seal is positioned radially inwardly from said platform of said component.

16. The gas turbine engine as recited in claim 13 , said second component having a second platform with a third mate face that is configured without either a trench or a cooling hole that opens into said trench.

17. A method of cooling a component of a gas turbine engine, comprising the steps of:
communicating a cooling airflow through a cavity located inside of the component;
extracting a portion of the cooling airflow from a radially extending portion of the cavity;
directly communicating the portion of the cooling airflow from the cavity into at least one cooling hole that is in fluid communication with the cavity; and
communicating the portion of the cooling airflow through an outlet of the at least one cooling hole that opens into a trench of a platform of the component.

18. The method as recited in claim 17 , wherein the portion of the cooling airflow travels axially along the trench to cool the platform.

19. The method as recited in claim 17 , wherein the portion of the cooling airflow travels axially along the trench prior to being returned to a core flow path of the gas turbine engine.

Assignees

• Teller Bret M
• Zelesky Mark F
• Lewis Scott D
• Spangler Brandon W
• Trindade Ricardo
• United Technologies Corp

Inventors

• Teller Bret M
• Zelesky Mark F
• Lewis Scott D
• Spangler Brandon W
• Trindade Ricardo

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D11/24

  by selectively cooling-heating stator or rotor components · CPC title

• F05D2240/81

  Cooled platforms · CPC title