FIELD: engines and pumps.
SUBSTANCE: gas turbine engine pipe assembly comprises a pipe, combustion chamber, suction holes, nozzle and bypass channel. Said pipe comprises inlet and outlet, inner and outer surfaces, and forms fluid flow passage between high-pressure turbine arranged inside pipe inlet end and low-pressure turbine located inside pipe outlet end. Combustion chamber is connected to pipe inlet section for pipe to receive flow from combustion chamber. Suction hole is arranged ahead of high-pressure turbine on pipe outer surface. Nozzle is arranged right behind high-pressure turbine and communicates with the pipe. Bypass channel has inlet and outlet ends, its inlet end being communicated with suction hole and its outlet being communicated with nozzle to form bypass fluid flow passage between said suction hole and nozzle. Other inventions of proposed set cover bypass pipe comprising bypass channel communicated with suction hole and nozzle, and gas turbine engine comprising above described assembly.
EFFECT: reduced power losses, higher efficiency.
12 cl, 1 dwg
