Patent ID: 8684668

Claim:
An impingement cooling insert for a turbine stator vane of a gas turbine engine, the impingement cooling insert comprising: a zigzag shaped main piece forming an alternating series of impingement cooling air channels and return air channels extending in a spanwise direction of a stator vane airfoil; a pressure side wall secured to a pressure side of the zigzag shaped main piece; a suction side wall secured to a suction side of the zigzag shaped main piece; an inlet cover plate secured to a top side of the zigzag shaped main piece; the top cover plate having cooling air supply openings that connect to the impingement cooling air channels; a bottom cap secured to a bottom side of the zigzag shaped main piece to block off the impingement cooling air channels and the return air channels; a row of impingement cooling air holes formed in the pressure side wall and connected to the impingement cooling air channels; a row of return air holes formed in the pressure side wall and connected to the return air channels; and, a row of impingement cooling air holes formed in the suction side wall and connected to the return air channels.