Gas turbine engine airfoil cooling circuit arrangement
A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, 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.
1. A component for a gas turbine engine, comprising:
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 extends inside of said airfoil, said at least one core cavity including a first plurality of axial ribs that are radially spaced along at least one inner wall of said at least one core cavity;
a baffle received within said at least one core cavity, said baffle including 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.
2. The component as recited in claim 1 , wherein the component is a turbine vane.
3. The component as recited in claim 1 , wherein each of said baffle, said plurality of pedestals and said first plurality of axial ribs are radially disposed within said airfoil.
4. The component as recited in claim 1 , comprising a plurality of augmentation features between each rib of said first plurality of axial ribs.
5. The component as recited in claim 1 , wherein said plurality of pedestals includes at least a first row of pedestals and a second row of pedestals, wherein said second row of pedestals is staggered relative to said first row of pedestals.
6. The component as recited in claim 1 , wherein at least one of said second plurality of axial ribs includes a break that divides said at least one of said second plurality of axial ribs into a first rib section and a second rib section.
7. The component as recited in claim 1 , comprising at least one discharge opening at said trailing edge of said airfoil.
8. The component as recited in claim 7 , wherein said at least one discharge opening extends through a pressure side of said airfoil.
9. The component as recited in claim 1 , comprising a leading edge core cavity that is fluidly isolated from said at least one core cavity.
10. The component as recited in claim 1 , wherein each of said plurality of pedestals are oblong shaped.
11. The component as recited in claim 1 , wherein said at least one core cavity is an intermediate cavity and comprising a leading edge core impingement cavity and a leading edge core down-pass cavity upstream from said intermediate cavity.
12. A component for a gas turbine engine, comprising:
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 extends inside of said airfoil;
a baffle received within said at least one core cavity;
a plurality of pedestals positioned adjacent to said at least one core cavity; and
a plurality of axial ribs positioned between said plurality of pedestals and said trailing edge of said airfoil; and
wherein said airfoil includes an inner diameter portion, an outer diameter portion and a mid-portion between said inner diameter portion and said outer diameter portion, and a portion of said plurality of axial ribs nearest to each of said inner diameter portion and said outer diameter portion are spaced a larger distance relative to one another than another portion of said plurality of axial ribs nearest said mid-portion.
13. A method of cooling a component of a gas turbine engine, comprising the steps of:
feeding a cooling airflow into a baffle disposed within a core cavity of an airfoil of the component;
feeding the cooling airflow through feed holes of the baffle;
after feeding the cooling airflow through the feed holes, communicating the cooling airflow between adjacent axial ribs of a first plurality of axial ribs such that the cooling airflow is compartmentalized between the first plurality of axial ribs;
communicating the cooling airflow across a plurality of pedestals; and
communicating the cooling airflow between adjacent ribs of a second plurality of axial ribs such that the cooling airflow is compartmentalized between the second plurality of axial ribs.
14. The method as recited in claim 13 , comprising the step of:
expelling the cooling airflow from the component to a core flow path of the gas turbine engine.
15. The method as recited in claim 14 , wherein the step of expelling includes communicating the cooling airflow through a discharge opening near a trailing edge of the airfoil.
16. The method as recited in claim 13 , comprising diverting a portion of the cooling airflow that is fed through the baffle through hardware that is separate from the airfoil.