FIELD: turbines.
SUBSTANCE: platform cooling device is intended for turbine rotary blade, having platform, located at interface boundary between aerodynamic profile and tail part, containing fasteners and shank, passing between fasteners and platform. Platform on its side, corresponding to aerofoil profile low pressure surface, has low pressure side, containing upper surface, passing from aerofoil profile base to low pressure side inclined surface, and overhangs above rear cavity formed in shank. Device comprises recess, collector channel and cooling channels. Recess is formed in platform lower surface area and has inlet, flow communicating with tail cavity. Collector channel passes from first end near low pressure side inclined surface to the second end near platform increased pressure side inclined surface and has connection with recess at its first end. Cooling channels are formed inside platform and run from connection point with recess or collector channel to holes, formed inside low pressure side inclined surface or platform rear edge.
EFFECT: invention provides effective and rational cooling area of turbine rotor blades platform.
25 cl, 8 dwg
