The application of electromagnetic impulse deicing (EIDI) systems to turbofan engine inlets on business aircraft has been investigated experimentally. The tests were performed in the Icing Research Tunnel at NASA's Lewis Research Center. The deicing system testbed was a Falcon Fanjet 20 engine nacelle. The effectiveness of various deicing coil configurations and mount designs were compared, and design parameters were developed specifically for EIDI systems in turbofan engines. Flight tests were also carried out at altitudes in the range 3000-6000 ft corresponding to a temperature range of -3 to -8 C. It is shown that the ice particles removed from the engine inlet by the deicing system were small enough for the engine to ingest. Tentative design specifications are given with respect to the optimum coil configuration, and operating power of a EIDI production candidate.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Electro-impulse de-icing of a turbofan engine inlet


    Contributors:

    Publication date :

    1985-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    The Effect of Crosswinds on Icing at Turbofan Engine Inlet

    Zheng, Mei / Yang, Qian / Dong, Wei et al. | SAE Technical Papers | 2019


    The Effect of Crosswinds on Icing at Turbofan Engine Inlet

    Yang, Qian / Guo, Zhiqiang / Zheng, Mei et al. | British Library Conference Proceedings | 2019