TURBINE BLADE WITH OPTIMIZED COOLING Russian patent published in 2019 - IPC F01D5/18 

FIELD: internal combustion engines.

SUBSTANCE: turbine blade of turbine engine, such as turbo-propeller or turbojet engine includes shank, blade supported by shank, passing in span direction, ending with end, and comprises front edge and rear edge located downstream of front edge, wall of discharge side and wall of suction side, located at a distance from each other and connecting each front edge with trailing edge. Blade comprises at least one channel configured to collect cooling air in the shank of the blade and to circulate it in a cooling loop; holes and/or slits made in its walls, to release cooling air from blade; an upper inner cavity located at the end of the blade to cool this end of the blade. Only one of said channels supplies cooling air collected in shank into upper cavity. Said channel is a direct supply channel, intended solely for supplying cooling air into upper inner cavity and comprises first inner side cavity, which extends along the pressure side wall, while being separated from the direct feed channel to form a heat shield which thermally isolates the direct feed channel from the delivery side wall.

EFFECT: invention is aimed at improving cooling efficiency.

13 cl, 8 dwg