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 immediately adjacent said first surface;

a plurality of pedestals interrupting a flow path through said skin core passage, the plurality of pedestals being distributed through the skin core passage;

at least one pedestal in the plurality of pedestals 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;

wherein said film cooling hole connects a first cooling air flow path of the plurality of cooling passages internal to said turbine engine component to said first surface;

wherein said skin core passage receives cooling air from a second cooling air flow path of the plurality of cooling passages 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. 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 immediately adjacent said first surface;

a plurality of pedestals interrupting a flow path through said skin core passage, the plurality of pedestals being distributed through the skin core passage; and

at least one pedestal in the plurality of pedestals 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 the one of said plurality of cooling passages is connected to said first surface via said film cooling hole and has a higher cooling air pressure than a cooling air pressure of said skin core passage.

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

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

5. The turbine engine component of claim 4 , wherein said at least one pedestal has the oblong cross section along a direction of flow through the skin core passage, the oblong cross section being one of an oval, a triangle, a rhombus, and an airfoil.

6. The turbine engine component of claim 4 , wherein at least 80% of a coolant entering said skin core passage exits said skin core passage at the aft edge.

7. The turbine engine component of claim 6 , wherein a remainder of the coolant entering the skin core passage exits the skin core passage at a radially outward facing surface of the turbine engine component.

8. The turbine engine component of claim 4 , wherein the turbine engine component is one of a blade outer air seal, 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.