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US 10,502,066 B2Granted
Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
AssigneeUnited Technologies Corporation
InventorScott D. Lewis
Life of this patent
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Abstract
A component for a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A skin core passage is defined immediately adjacent the first surface, and at least one pedestal interrupts a flow path through the skin core passage.
Claims15
A turbine engine component comprising:
- a fore edge connected to an aft edge via a first surface and a second surface;
- a plurality of cooling passages defined within the turbine engine component;
- a skin core passage defined within an exterior wall of the turbine engine component and immediately adjacent said first surface;
- and
- at least one pedestal interrupting a flow path through said skin core passage;
- wherein said at least one pedestal comprises a plurality of pedestals distributed through said skin core passage;
- wherein said at least one pedestal includes a film cooling hole defined at least partially within the at least one pedestal, the film cooling hole connecting one of said plurality of cooling passages to said first surface;
- and
- wherein said film cooling hole connects a first cooling air flow path internal to said turbine engine component to said first surface, and wherein said skin core passage receives cooling air from a second cooling air flow path internal to said turbine engine component, and wherein said second cooling air flow path is a low pressure cooling air flow path relative to said first cooling air flow path.
6 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor section fluidly connected to the compressor section by a flowpath;
- a turbine section fluidly connected to the combustor section by the flowpath;
- at least one gas turbine engine component exposed to a fluid passing through said flowpath, the at least one gas turbine engine component including:
- a first surface and a second surface;
- at least one cooling passage defined within the turbine engine component;
- a skin core passage defined within an exterior wall of the at least one gas turbine engine component and immediately adjacent said first surface;
- and
- at least one pedestal interrupting a flow path through said skin core passage, the at least one pedestal connecting an interior surface of said at least one cooling passage to said first surface;
- wherein the at least one cooling passage includes a first cooling passage and a second cooling passage, and the at least one pedestal connects the interior surface of the first cooling passage to said first surface;
- and
- wherein the first cooling passage receives a first cooling air from a first source, the second cooling passage receives a second cooling air from a second source, and wherein the skin core passage receives the second cooling air from the second cooling passage.
9 more elements
Dependencies are inferred from the claim text.