A method for controlling a pressure control mechanism in a turbofan engine having a precooler permitting heat exchange between ambient air and bleed air includes detecting at least one of an engine failure or a bleed system failure, detecting at least one of an ice condition or an activation of an anti-ice system, and actuating the pressure control mechanism, thereby altering the heat exchange between the ambient air and the bleed air.
SYSTEM AND METHOD FOR OPERATING A PRECOOLER IN AN AIRCRAFT
2017-06-29
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
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