FIELD: aviation.
SUBSTANCE: turbo-compressor system for extracting energy from an aircraft engine. Turbo-compressor system has a turbo-compressor unit with a turbine mechanically connected to at least one compressor. Turbo-compressor system has a turbo-compressor inlet that is in fluid communication with an air intake system of an aircraft engine, and a turbo-compressor outlet, which is in fluid communication with an conditioning unit of the aircraft air conditioning system and is configured to extract bleed air at a lower temperature entering the unit from the turbo-compressor unit in said air conditioning unit. Turbo-compressor system has a ram air inlet connected to said at least one compressor. Turbo-compressor system has a turbo-compressor control valve and a turbo-compressor check valve or a turbo-compressor shut-off valve, both of which are connected to the turbo-compressor unit through a plurality of connecting ducts.
EFFECT: turbo-compressor system is designed to extract energy from bleed air to reduce bleed air flow and to use ram air by an air conditioning unit.
24 cl, 13 dwg
