Patent ID: 8517680

Claim:
An air cooled turbine rotor blade comprising: an airfoil section extending from a platform; the platform having a forward side and an aft side; the platform having a pressure side and a suction side that both form a mate-face gap with an adjacent turbine rotor blade platform; a first platform cooling zone formed on a pressure side of the platform; a second platform cooling zone formed on a forward end of the suction side of the platform; a third platform cooling zone formed on an aft end of the suction side of the platform; the three platform cooling zones each being formed with a series of ribs that form a series of impingement chambers, and with each rib including a row of impingement holes; and, a cooling air supply hole connected to each of the three platform cooling zones at a forward location of each of the three platform cooling zones to supply cooling air from a dead rim cavity to each of the three platform cooling zones.