Cooling features for a component of a gas turbine engine

A component for a gas turbine engine, comprising:

• at least one internal cavity defined by an outer wall and an inner wall, the at least one internal cavity extending through the component, the at least one internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
• a first plurality of cooling features extending from a surface of the outer wall, each of the first plurality of cooling features having a chevron shape extending in a first direction;
• and
• a second plurality of cooling features extending from a surface of the inner wall, each of the second plurality of cooling features having a chevron shape extending in a second direction, the first direction being opposite to the second direction, and the first plurality of cooling features being in a facing spaced relationship with respect to the second plurality of cooling features.

A gas turbine engine, comprising;

• at least one component configured to receive a cooling air flow;
• at least one internal cavity defined by an outer wall and an inner wall, the at least one internal cavity extending circumferentially across the component from a blade arrival edge to a blade departure edge, the at least one internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
• a first plurality of cooling features extending from a surface of the outer wall, each of the first plurality of cooling features having a chevron shape or serpentine shape extending in a first direction;
• and
• a second plurality of cooling features extending from a surface of the inner wall, each of the second plurality of cooling features having a chevron shape or serpentine shape, and the first plurality of cooling features being in a facing spaced relationship with respect to the second plurality of cooling features.