Optimisation of a Nacelle Electro-Thermal Ice Protection System for Icing Wind Tunnel Testing
نویسندگان
چکیده
Abstract Aircraft are equipped with ice protection systems (IPS), to avoid, delay or remove accretion. Two widely used technologies the thermo-pneumatic IPS and electro-thermal (ETIPS). Thermo-pneumatic requires air extraction from engine negatively affecting its performances. Moreover, in context of green aviation, aircraft manufacturers moving towards hybrid fully electric requiring all on-board systems. In this work, an ETIPS has been designed optimised replace nacelle pneumatic-thermal system. The aim is minimise power consumption while assuring limited null formation that surface temperature remains between acceptable bounds avoid material degradation. design parameters were length heat flux each heater. Runback formations assessed by means in-house developed PoliMIce framework. optimisation was performed using a genetic algorithm, constraints handled through linear penalty method. optimal configuration required 33% less respect previously installed IPS. Furthermore, performance not affected case ETIPS. This energy saving resulted estimated reduction specific fuel 3%, when operating anti-icing mode.
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ژورنال
عنوان ژورنال: Prace Instytutu Lotnictwa
سال: 2023
ISSN: ['2545-2835', '2300-5408', '0509-6669']
DOI: https://doi.org/10.2478/tar-2023-0004