Abstract: A passively cooled blade platform for a gas turbine rotor adapted for rotation about an axis within a stationary coolant fluid. The platform has a radially outer surface defining an annular gas path, a radially inner surface in flow communication with the coolant fluid, a leading edge, and a trailing edge. The inner surface includes at least one cooling flow channel in the inner surface. Each channel has a flow path from a channel inlet to a channel outlet, preferably with a tangential component at the inlet opposite to the direction of rotation and an axial component at the outlet. The flow channels are defined by ribs or pedestals extending radially inwardly from the platform inner surface to direct cooling fluid flow and create turbulence to dissipate heat from the platform on exposure to cooling fluid flow.

Abstract: A passively cooled blade platform for a gas turbine rotor adapted for rotation about an axis within a stationary coolant fluid. The platform has a radially outer surface defining an annular gas path, a radially inner surface in flow communication with the coolant fluid, a leading edge, and a trailing edge with at least one cooling flow channel in the inner surface. Each channel has a flow path from a channel inlet to a channel outlet, with a tangential component at the inlet opposite to the direction of rotation and an axial component at the outlet. The flow channels are defined by ribs or pedestals extending radially inwardly from the platform inner surface to direct cooling fluid flow and create turbulence. The ribs reinforce the platform structurally, and together with the pedestals serve to dissipate heat from the platform on exposure to cooling fluid flow.