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US 10,370,981 B2Granted
Gas turbine engine component cooling circuit with respirating pedestal
AssigneeUnited Technologies Corporation
InventorsThomas N. Slavens, Brooks E. Snyder
Life of this patent
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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.
Claims12
A component, comprising:
- an airfoil section having an outer wall and an inner wall;
- and
- a pedestal that traverses across a flow channel from said outer wall to said inner wall, said flow channel disposed between said outer wall and said inner wall, said pedestal including a body and a head that extends transversely from said body, said head including at least one interior bore in fluid communication with said flow channel, and said body including a second bore extending from said head to said inner wall,
- wherein said at least one interior bore is configured to receive a cooling fluid from said flow channel and communicate said cooling fluid inside of said pedestal through said second bore and into a cavity formed inside of said inner wall.
1 more element
A gas turbine engine, comprising:
- an airfoil including a cooling circuit configured to cool said airfoil with a cooling fluid, said cooling circuit including:
- a flow channel disposed between an outer wall and an inner wall of said airfoil and
- a pedestal that extends from said outer wall to said inner wall across said flow channel between said outer wall and said inner wall, wherein said pedestal includes a hollow portion in fluid communication with said flow channel, wherein said pedestal includes a body and a head that extends transversely from said body, said head including at least one interior bore fluidly connecting said flow passage with said hollow portion,
- wherein said flow channel connects between a first cavity and a second cavity formed inside of said airfoil, and said at least one interior bore is configured to receive a cooling fluid from the flow channel and communicate said cooling fluid inside said pedestal through said hollow portion and into a third cavity opposite said flow channel from said inner wall.
1 more element
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 disposed within an airfoil of the gas turbine engine component, wherein the flow channel is disposed between an outer wall and an inner wall of said airfoil;
- cooling the first cooling fluid with a second cooling fluid that is communicated in a second direction generally perpendicular to the first direction inside a pedestal that traverses across the flow channel from the outer wall to the inner wall, wherein the pedestal includes a head and a body that extends transversely from the head;
- extracting the second cooling fluid from the first cooling fluid inside of the flow channel through the head;
- communicating the second cooling fluid through the body in the second direction;
- and
- expelling in said second direction the second cooling fluid into an inner cavity formed within the inner wall of said airfoil.
3 more elements
Dependencies are inferred from the claim text.