Patent ID: 9656756
Date: 2017-05-23
CPC Classifications: B64D,F02C,F25B,Y02T

Claim:
1. A turbo-compressor (TC) system for extracting energy from an aircraft engine, the turbo-compressor system comprising: a turbo-compressor assembly comprising a turbine mechanically coupled to at least one compressor; a turbo-compressor inlet in fluid communication with a bleed air system in the aircraft engine, to intake bleed air from the bleed air system into the turbo-compressor assembly; a turbo-compressor outlet in fluid communication with an air conditioning pack of an aircraft air conditioning system, to extract reduced temperature pack inlet air from the turbo-compressor assembly directly into the air conditioning pack, the reduced temperature pack inlet air comprising one of, a mixture of turbine outlet air and compressor outlet air, and a mixture of turbine outlet air, compressor outlet air, and bleed air through a pack flow control valve for the air conditioning pack, the air conditioning pack being separate from the turbo-compressor assembly and further cooling the reduced temperature pack inlet air, and the air conditioning pack being coupled to a pack heat exchanger having one or more heat exchangers; the at least one compressor coupled to at least one of, a ram air inlet to intake ram air by the at least one compressor, and a recirculated cabin air duct to intake recirculated cabin air from an aircraft cabin by the at least one compressor; and, a turbo-compressor control valve, and a turbo-compressor check valve or a turbo-compressor shutoff valve, both coupled to the turbo-compressor assembly via a plurality of connective ducts, wherein the turbo-compressor system extracts energy from the bleed air.