Abstract
The phenomenon of mixed phase/ice crystal ice accumulation widely exists in the icing process of aero-engine inlet system. It is urgent to investigate the internal icing of aero-engine inlet system and ensure flight safety to carry out the corresponding calculation method and systematically analyze the icing characteristics of mixed phase/ice crystal. The aero-engine flow field model, the mixed phase sticking model, the mixed phase impact model and the ice accretion model under the condition of mixed phase icing are established for the aero-engine inlet system (Nacelle, Nosecone, Fan, Bypass, IGV). Moreover, the effects of different air velocity, liquid water content/total water content (LWC/TWC) and water droplet diameter changes on the icing mass capture of each component of the aero-engine inlet system and the changes of ice growth of each component were investigated. The results show that mass capture on nacelle and nosecone surfaces increases with the increase of airflow velocity. For the bypass surface, mass capture with 90% span is 16.84% of mass capture with 30% span when s/c = 0 and the airflow velocity is 200 m/s. Mass capture on the nacelle surface increases with the increase of melting rate. As the diameter of the droplets increases, the mass capture on both the nacelle and nosecone surfaces increase. At droplet diameter is 100 μm, mass captures at s/c = 0 at 30% and 90% IGV spans are 0.005 and 0.0153 kg/m2 s, respectively. Ice growth is most severe at the front of the nosecone. Under the same airflow velocity, the ice growth of fan, bypass and IGV increases significantly with the increase of span. Finally, through the analysis of mixed phase icing characteristics of aero-engine inlet system, it is necessary to design anti-icing of aero-engine inlet system. Meanwhile, in the anti-icing design, it is necessary to pay attention to the pressure side of the fan, the bypass surface and the IGV as well as the area with large span.
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