Gas turbine engine component cooling circuit with respirating pedestal

Patent metadata

Field	Value
Publication number	US-2016333702-A1
Application number	US-201515112497-A
Country	US
Kind code	A1
Filing date	Jan 26, 2015
Priority date	Feb 13, 2014
Publication date	Nov 17, 2016
Grant date	—

Abstract

A component according to an exemplary aspect of the present disclosure includes, among other things, a pedestal that traverses a flow channel disposed between a first wall and a second wall. The pedestal includes at least one interior bore configured to communicate a cooling fluid inside of the pedestal.

First claim

What is claimed is:

1 . A component, comprising:
a pedestal that traverses a flow channel disposed between a first wall and a second wall; and said pedestal including at least one interior bore configured to communicate a cooling fluid inside of said pedestal.

2 . The component as recited in claim 1 , wherein said component is one of a blade, a vane, a shroud, a blade outer air seal (BOAS), a combustor liner and a turbine exhaust case liner.

3 . The component as recited in claim 1 , wherein said at least one interior bore feeds said cooling fluid from a cavity inside of said second wall.

4 . The component as recited in claim 1 , wherein a head of said pedestal is received in a trough formed in said first wall.

5 . The component as recited in claim 1 , wherein said at least one interior bore feeds said cooling fluid to a cavity inside of said second wall.

6 . The component as recited in claim 1 , wherein said pedestal is disposed at a leading edge region or a trailing edge region of said component.

7 . The component as recited in claim 1 , wherein said first wall is an outer wall and said second wall is an inner wall.

8 . The component as recited in claim 1 , wherein said pedestal includes a body and a head that extends transversely from said body.

9 . The component as recited in claim 8 , wherein at least one of said head and said body includes said at least one interior bore.

10 . The component as recited in claim 1 , comprising a plurality of pedestals arranged in rows inside of said component, each of said plurality of pedestals traversing said flow channel.

11 . A gas turbine engine, comprising:
a component that defines a cooling circuit configured to cool said component with a cooling fluid, said cooling circuit including:
a flow channel disposed between a first wall and a second wall of said component; and
a pedestal that extends across said flow channel.

12 . The gas turbine engine as recited in claim 11 , wherein said flow channel is a microcircuit.

13 . The gas turbine engine as recited in claim 11 , wherein said cooling circuit is disposed inside an airfoil of said component.

14 . The gas turbine engine as recited in claim 11 , wherein said flow channel connects between a first cavity and a second cavity formed inside of said component.

15 . The gas turbine engine as recited in claim 11 , wherein said cooling circuit excludes film cooling holes.

16 . A method of cooling a gas turbine engine component, comprising:
communicating a first cooling fluid in a first direction through a flow channel of a cooling circuit of the gas turbine engine component; and cooling the first cooling fluid with a second cooling fluid that is communicated in a second, different direction inside a pedestal that traverses the flow channel.

17 . The method as recited in claim 16 , comprising expelling the second cooling fluid into a cavity of the cooling circuit.

18 . The method as recited in claim 16 , comprising:
communicating the first cooling fluid within a first cavity of the cooling circuit; communicating the first cooling fluid across the pedestal within the flow channel; and expelling the first cooling fluid into a second cavity of the cooling circuit.

19 . The method as recited in claim 16 , wherein the second cooling fluid is extracted from the first cooling fluid inside of the flow channel.

20 . The method as recited in claim 16 , wherein the gas turbine engine component is cast using a casting article that is manufactured layer-by-layer using an additive manufacturing process.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Snyder Brooks E

Classifications

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F01D25/12

  Cooling · CPC title

• F23R3/002

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

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title