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US 10,329,923 B2Granted
Gas turbine engine airfoil leading edge cooling
AssigneeUnited Technologies Corporation
InventorsThomas N. Slavens, Dominic J. Mongillo, Jr., Matthew A. Devore
Life of this patent
Estimating the term…
Abstract
An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
Claims19
A gas turbine engine component, comprising:
- an airfoil having a leading edge area that corresponds to a stagnation traverse region of the airfoil;
- a first circuit to cool a first section of the leading edge area;
- and
- a second circuit to cool a second section of the leading edge area, the first circuit separate and distinct from the second circuit within the airfoil.
1 more element
A gas turbine engine, comprising:
- an airfoil;
- a variable vane array upstream from the airfoil;
- a first circuit within the airfoil to cool a leading edge area of the airfoil;
- and
- a second circuit within the airfoil to cool a leading edge area of the airfoil, wherein the leading edge area corresponds to a stagnation traverse region of the airfoil.
2 more elements
A method of cooling an airfoil, comprising:
- communicating a cooling flow to a leading edge area of an airfoil through both a first cooling circuit and a second cooling circuit that is separate and distinct from the first cooling circuit within the airfoil, the leading edge area corresponding to a stagnation traverse region of the airfoil.
Dependencies are inferred from the claim text.