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Abstract
In order to reduce the fuel penalty and engine bleed air capacity, under the premise of satisfying cooling and pressure stability demands for airtight cabin, a new half-closed loop air cycle system (ACS) driven by a power turbine was presented. To verify the cooling capacity of this new system, a simulation investigation based on LMS AMESim software was carried out. The simulation modules of turbine cooler, ejector, water separator and heat ex-changers have been established. To avoid the ice barrier at condenser outlet, the heat transfer efficiencies of regenerator and condenser were set at 0.25~0.30. Using the same cooling capacity of F-22 fighter's ACS package as the design parameter, the engine bleed air was found to decrease up to 45% for this new half-closed loop ACS when compared to the open-type ACS in theory.
Published Version
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