Patent ID: 8322988

Claim:
An impingement cooling insert for cooling an inner wall of an airfoil used in a gas turbine engine, the impingement cooling insert comprising: a first plate having an airfoil shape with a pressure side and a suction side and a leading edge region and a trailing edge region; a second plate having an airfoil shape with a pressure side and a suction side and a leading edge region and a trailing edge region; the first and second plates each having hook receiving slots formed on the pressure side and the suction side and the leading edge region that divide each plate into a forward pressure side chamber and an aft pressure side chamber and a forward suction side chamber and an aft suction side chamber; the first plate having a first row of impingement cooling air holes on the forward pressure side chamber and a second row of impingement cooling air holes on the aft suction side chamber and a third row of impingement cooling air holes on the forward suction side chamber; the second plate having a fourth row of impingement cooling air holes on the aft pressure side chamber; the first plate having a first and a second cooling air collection chamber in the aft pressure side chamber; the second plate having a third cooling air collection chamber in the forward pressure side chamber; the first cooling air collection chamber being connected to the third row of impingement cooling air holes; the second cooling air collection chamber being connected to the second row of impingement cooling air holes; the third cooling air collection chamber being connected to the fourth row of impingement cooling air holes; and, the first row of impingement cooling air holes being connected to a cooling air supply cavity formed within each of the two plates.