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

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.