Patent ID: 8622701

Claim:
A turbine rotor disk for a gas turbine engine comprising: a rotor disk with a plurality of slots each to receive a turbine rotor blade; a radial extension formed on the rotor disk between adjacent slots; a cooling air chamber formed within the radial extension and connected to a cooling air supply channel; a plurality of impingement cooling holes connected to the cooling air chamber; the turbine rotor blade secured within the slot of the rotor disk; the rotor blade having a platform extending over the impingement cooling holes of the cooling air chamber; the impingement cooling holes are directed to discharge impingement cooling air to a backside surface of the platform; the cooling air chamber and the cooling air supply channel are formed on one side of the rotor disk; and, a cover plate is secured to the side of the rotor disk and encloses both the cooling air chamber and the cooling air supply channel.