Gas turbine engine airfoil cooling circuit arrangement
AssigneeRaytheon Technologies Corporation
InventorsShawn J. Gregg, Dominic J. Mongillo, Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer
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Abstract
A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
Claims10
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor section;
- and
- at least one of said compressor section and said turbine section including a component having an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of said airfoil, wherein said cooling circuit includes:
- at least one core cavity that radially extends inside said airfoil and includes a first plurality of axial ribs;
- a baffle received within said at least one core cavity, wherein said baffle includes a convex side and a concave side, and each of said convex side and said concave side include a plurality of feed holes, and said plurality of feed holes of said convex side are larger than said plurality of feed holes of said concave side;
- a plurality of pedestals positioned adjacent to said at least one core cavity;
- and
- a second plurality of axial ribs positioned between said plurality of pedestals and said trailing edge of said airfoil.
Dependencies are inferred from the claim text.