TURBINE BLADE WITH OPTIMIZED COOLING OF ITS TRAILING EDGE, COMPRISING CHANNELS LOCATED UPSTREAM AND DOWNSTREAM AND INNER SIDE CAVITIES Russian patent published in 2019 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: turbine blade turbine engine, such as a turbo-propeller or turbojet engine, includes a shank, a shank supported by a shank, having a leading edge and a trailing edge located downstream of the leading edge, wall of delivery side and wall of suction side, located at a distance from each other, which connect front edge with trailing edge. Feather comprises at least one upstream duct for cooling the leading edge, at least one downstream channel separated from the upstream duct for cooling the trailing edge and an inner lateral cavity. Inner lateral cavity extends along pressure side wall to form heat shield extending from blade root to its end. Heat shield has a width sufficient to simultaneously isolate the upstream channel and the downstream channel from the delivery side wall.

EFFECT: invention is aimed at improving cooling efficiency.

8 cl, 6 dwg