TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING

An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined atleast partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radiallyoutboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50),before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c). The impinged area (60) may include a turbulator (70) to enhance heat transfer. 本发明涉及用于涡轮机转子叶片（10）的集成式翼型部和平台冷却系统（30），其包括多个蜿蜒的冷却支腿（32a、32c、42a、42c），冷却支腿（3