Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

A gas turbine engine component, comprising:

• a pressure side comprising an interior surface;
• a suction side comprising an interior surface;
• a trailing edge portion;
• a plurality of suction side and pressure side impingement orifices disposed in the trailing edge portion,
• wherein each suction side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the suction side interior surface,
• wherein each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto a target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface,
• wherein at least one chevron arrangement comprises a plurality of chevrons, a tip of each chevron of the plurality of chevrons being disposed in the respective target area and wings of the chevrons of the plurality of chevrons forming at least one groove there between in which spent cooling air flows.