Patent ID: 9555893
Date: 2017-01-31
CPC Classifications: B64D,F25B,Y02T

Claim:
1. An aircraft air provision system comprising: a power turbine that receives bleed air, the power turbine providing rotational energy to a shaft and outputs output air at an intermediate pressure, the bleed air received from a first source consisting of a compressor section of an engine; a compressor coupled to the shaft that receives input air from the compressor section of the engine, the compressor outputting compressed air having a pressure equal to the intermediate pressure; a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed; a second heat exchanger in fluid communication with an output of the mix chamber, the second heat exchanger receiving ram air from a ram air scoop for mixing with the output of the mix chamber; a second fan coupled to the shaft, wherein the second fan draws air through the second heat exchanger; a cooling turbine coupled to the shaft and that is in fluid communication with an output of the second heat exchanger; and a precooling heat exchanger in fluid communication with an input of the power turbine and configured to cool air exiting the compressor section, wherein the precooling heat exchanger utilizes air from a first fan of the engine to cool air exiting the compressor section, wherein the bleed air is received from an output of the precooling heat exchanger.