TURBINE BLADE COMPRISING COOLING SYSTEM Russian patent published in 2021 - IPC F01D5/18 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to aircraft turbine blade comprising radial cavities of trough and back cavities and at least one central cavity, located in the central part of the blade and surrounded by trough cavities and back cavities, wherein the blade also includes cooling systems, wherein at least the first cooling system comprises: first cavity (A) and second cavity (B), wherein first and second cavities are interconnected at level of inner radial end (14) and outer radial end (16) of blade, third cavity (C) communicating with second cavity (B) at level of outer radial end (16), fourth cavity (D) communicating with third cavity (C) at level of inner radial end (14). First cavity (A) and second cavity (B) are made so as to simultaneously receive cold air supply through common inlet air hole at the level of inner radial end (14) and that air passes in them in one direction in radial direction, wherein first cavity (A) is cavity of trough, second cavity (B) is central cavity, third cavity (C) and fourth cavity (D) are cavities of back.

EFFECT: disclosed is a turbine blade comprising a cooling system.

8 cl, 9 dwg