ROTOR BLADE WITH ONE OR MORE SIDE WALL COOLING CIRCUITS

摘要

A rotor blade for a gas turbine engine includes an airfoil and a cooling microcircuit. The airfoil includes a first side wall, a second side wall and a tip endwall, where the first side wall and the second side wall extend to and cooperate to form the tip endwall, defining a main cavity between the first side wall and the second side wall. The cooling microcircuit includes a microcircuit cavity, an inlet, a side wall outlet and a tip outlet. The microcircuit cavity is embedded within the first side wall, and the inlet extends from the main cavity to the microcircuit cavity. The side wall outlet extends from the microcircuit cavity to an exterior first side surface of the airfoil. The tip outlet extends from the microcircuit cavity to an exterior tip surface of the airfoil.