Turbine engine component including an axially aligned skin core passage interrupted by a pedestal

1. 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.

2. The turbine engine component of claim 1 , wherein said at least one pedestal has an oblong cross section relative to a radius of a turbine engine including the turbine engine component.

3. The turbine engine of claim 2 , wherein each of said oblong cross sections includes a longest diameter, and said longest diameter is aligned with an axis of the turbine engine.

4. The turbine engine of claim 2 , wherein each of said oblong cross sections includes a longest diameter, and said longest diameter is aligned with a radius of the turbine engine.

5. The turbine engine of claim 1 , wherein each of said pedestals has a cross section along a direction of flow through the skin core passage, the cross section being one of an oval, a triangle, a rhombus, an airfoil, and a circle.

6. The turbine engine of claim 1 , wherein at least 80% of the cooling air entering said skin core passage exits said skin core passage at the aft edge.

7. The turbine engine of claim 6 , wherein the skin core passage defines an axial coolant flow path.

8. The turbine engine of claim 1 , wherein the turbine engine component is one of a blade outer air seal, a combustor liner, a blade, and a vane.

9. The turbine engine component of claim 8 , wherein the blade is a blade in a second or later turbine stage.

10. 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.

11. The gas turbine engine of claim 10 , further comprising a film cooling hole defined within said at least one pedestal, the film cooling hole providing a flow path between said at least one cooling passage to said first surface.

12. The turbine engine of claim 6 , wherein at least 95% of the cooling air entering the skin core passage exits the skin core passage at the aft edge.

13. The turbine engine of claim 1 , wherein the skin core passage conforms with a contour of the first surface.

14. The turbine engine of claim 13 , wherein each of an inward facing wall and an outward facing wall of the skin core passage conforms with the contour of the first surface.

15. The turbine engine of claim 1 , wherein the skin core passage is a convective cooling passage.