TURBOFAN REDUCER ENGINE, WHICH IS EQUIPPED WITH THE LOW PRESSURE SYSTEM FOR CONTROLLING THE AIRCRAFT ENVIRONMENT Russian patent published in 2018 - IPC F02C6/08 F02C7/32 F02C9/18 

FIELD: aviation.

SUBSTANCE: invention relates to aviation. Gas turbine engine assembly includes the fan compartment, the compressor compartment, the combustion chamber and the pylon. Engine also includes the low pressure system (30) for monitoring the environment of the aircraft. Mentioned system (30) comprises the high pressure outlet (34) in the high pressure area in the main compressor compartment and the low pressure outlet (32) in the low pressure area. Low pressure outlet (32) is connected to the first duct (36) that leads to the exhaust opening and to the compressor compartment (54) of the turbocharger (42). High pressure outlet (34) leads to the turbine compartment (52) of the turbocharger (42) so that the air in the high pressure outlet (34) leads to the turbine compartment (52), which in turn drives the compressor compartment (54) of the turbocharger. Combined output (44) of the compressor compartment and the turbine compartment of the turbocharger mixes and passes the output flow for its delivery and use on board of the aircraft. System also includes the valve (38), which is located between the low pressure outlet (32) and the compressor compartment (54) of the turbocharger (42).

EFFECT: invention improves the efficiency of the engine.

18 cl, 3 dwg