COOLED BLADE OF GAS TURBINE Russian patent published in 2021 - IPC F01D5/18 F01D9/02 

FIELD: machine building.

SUBSTANCE: invention relates to turbine construction, namely, to a cooled gas turbine blade intended mainly for operation in the field of high temperatures. Cooled blade of gas turbine includes hollow feather (1) made in the form of front cavity (2) and rear cavity (3) separated by radial partition (4). In front cavity (2) there is front deflector (5) fixed by the first transverse ribs (6) on the walls of hollow feather (1) on the side of the back and the trough. In rear cavity (3) there is rear deflector (7) fixed by the second transverse ribs (8) on the walls of hollow feather (1) on the side of the back and the trough. In front deflector (5) there are holes for jet cooling (9) of inlet edge and walls of front cavity. In back deflector (7) holes of jet cooling (10) of rear cavity walls are made. In front cavity (2) in walls of hollow feather (1) there are holes of film cooling (11). In slot channel of outlet edge (12) along height of walls of hollow feather there are rows of pins (13) with diameter D_pin. Pins (13) are arranged in staggered order. Ratio of the cross-S₁ and S₂ of the longitudinal pitch setting pins to the diameter D_pin is 2.5. On walls of hollow feather (1) on back and trough side there are rear ribs (14). Rear ribs (14) have a carbon form with an opening angle of 120°. Ratio of the thickness b_p, height h_p and the width l_p of the rear edges to the diameter D of pin pieces (13) is 0.20–0.30, 0.12–0,33, and 1.1–1.3, respectively. Ratio of distance from axis of pin (13) to vertex of angle of rear rib S_p to diameter of pin D_pin is 0.9-1.2.

EFFECT: technical result consists in improvement of cooling efficiency of gas turbine blades.

1 cl, 7 dwg