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

FIELD: machine building.

SUBSTANCE: cooled blade of gas turbine comprises hollow feather made in the form of front and rear cavities separated by radial partition. In the front cavity there is a front deflector, in the rear cavity – a rear deflector. In front deflector there are holes for jet cooling of leading edge and walls of front cavity. In back deflector there are holes for jet cooling of rear cavity walls. In front cavity 2, in hollow airfoil 1 walls, the film cooling holes 11 are made. In slot channel of outlet edge along height of walls of hollow feather on side of back and trough there are longitudinal grooves of constant cross section, having the shape of circular segment, with depth H_c and width B_c. In longitudinal grooves opposing on the side of the back and the trough there are rows of pins with diameter D_p staggered. Ratio of transverse S₁ and longitudinal S₂ their mounting pitch to diameter D_p pins is 2.5. Ratio of depth H_c of longitudinal grooves to diameter D_p of pins is in range from 0.25 to 0.75, and ratio of width B_c of longitudinal groove to diameter D_p pins is in range from 1.5 to 2. At that, cross-sections of longitudinal grooves on the back side are formed by circles, centres O₁ which lie on pins axes. Cross-sections of longitudinal grooves on the side of the trough are formed by circles, centres O₂ which lie on the normal to the inner surface of the trough.

EFFECT: invention is aimed at reduction of blade wall temperature by intensification of heat transfer in slot channel of outlet edge.

1 cl, 7 dwg