TURBOJET TURBINE STAGE BLADES AIR-LIQUID COOLING SYSTEM Russian patent published in 2020 - IPC F01D5/00 F01D5/12 F01D5/14 F01D5/18 F01D5/02 F01D5/08 F02C7/00 F02C7/12 F02C7/16 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to the field of aircraft engine building of gas turbines, namely to turbojet engines turbines cooling, in particular to the straightening blades cooling device, turbine blades and impeller intended mainly for operation in the field of high temperatures, maximum engine rpm and afterburner. Outboard air (21), which is cleaned from foreign impurities by centrifugal filter (20) and filter of fine cleaning of outboard air (17), is supplied via air duct (13) and air duct (22) into housing (26). Further, cleaned air is forced through channels (31, 32, 33, 38, 40, 41) through holes in annular flanges with sealing seals of first, second stages of turbine (50, 51, 52, 53, 54, 55) and arrives in straightening vanes (6, 8). When engine rpm increases from cruise to maximum and afterburner is added to impeller and turbine vanes, coolant is fed proportionately to pressure pump by coolant with reverse motor (15).

EFFECT: improved cooling of turbojet engines turbines at various operation modes.

1 cl, 2 dwg