Blended flow air cycle system for environmental control
An aircraft air provision system includes a power turbine that receives bleed air at a first pressure and provides rotational energy to a shaft and outputs output air at an intermediate pressure. The system also includes a compressor coupled to the shaft that receives input air at a second pressure that is lower than the first pressure and outputs compressed air having a pressure equal to the intermediate pressure and a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed. The system also includes a cooling turbine coupled to the shaft and that is in fluid communication with an output of the mix chamber.
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.
2. The system of claim 1 , wherein the input air is received from a ram air scoop.
3. The system of claim 1 , further comprising:
a cabin air recirculation system coupled to an output of the cooling turbine.