COOLED TURBINE BLADE ELEMENT Russian patent published in 2019 - IPC F01D5/18 

FIELD: turbines or turbomachines.

SUBSTANCE: cooled turbine blade element (1) comprises cooling air channel (4) made inside blade in radial direction along inlet edge (5), connected by inlet convergent in direction of cooling air flow channels (6) through dispensing header (7) with supply channel, and outlet channels (8) with outer surface of blade (3). Inlet confuser (6) and outlet channels (8) are made tangentially relative to cooling air channel (4), which is equipped with transit pipeline (9) installed eccentrically inside it, with variable gap relative to its inner wall (10). In flow direction of air flow in cooling channel (4) there is confuser short curvilinear channel (12), on inner wall (10) of which in zone of inlet edge (5) spherical recesses (11) are made in radial direction, which is connected to input convergent channels (6), forming common channel with ratio of total cross-sectional areas at input to input (6) and output channels (8) in interval 1.4<F_{in.chan.in.sec.}/F_{out.chan.in.sec.}<1.8. Output channels (8) are cylindrical with diffuser outlet sections, length of which relative to length of output channels (8) is l_d=0.5L. In addition, geometrical parameters of location and dimensions of spherical recesses are determined.

EFFECT: invention allows to reduce thermal stresses and increase blades working life.

4 cl, 3 dwg