FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises fan, compressor, combustion chamber, high-pressure turbine, low-pressure turbine, first and second air bleed circuits. Compressor incorporates sets of compressor vanes to increase pressure sequentially in appropriate stages. High-pressure turbine represents a single-stage turbine with nozzle provided with the set of stator vanes and rotor vanes arranged there behind. Every said vane has pressure and suction sides opposed along periphery and extending radially and axially along chord between opposite front and rear edges. Hollow vane has blank web jointing said opposed sides to make front and rear cooling channels. Said channels feed appropriate first cooling holes arranged along front edges and second cooling holes made along rear edge. First cooling air bleed circuit is arranged to communicate compressor last stage and vane front channels to supply compressed primary air at first pressure. Second cooling air bleed circuit is arranged to communicate compressor intermediate stage and vane rear channels to supply compressed secondary air at second pressure. Second pressure is lower than first pressure. Intermediate stage feed secondary air at pressure higher than static pressure in combustion product gases at rear edges to allow for reverse flow reserve in second holes. This invention covers also method of cooling nozzle vanes by bleeding primary air from compressor last stage into front cooling channels for delivery of said air from first holes. Secondary air is bled from compressor intermediate stage into rear cooling channels for delivery from second holes.
EFFECT: higher engine efficiency.
9 cl, 6 dwg
