Transactions of Nanjing University of Aeronautics & Astronautics
Three-Dimensional Numerical Simulation of Ice Accretion on Rotating Components of Engine Entry
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Abstract:
The rotating engine components subject to Coriolis and centrifugal forces exhibit distinctive ice accretion characteristics when an aircraft operates under supercooled large droplet conditions. This study establishes the mathematical model of the ice accretion on rotating components of engine entry and considers the dynamic characteristics of terminal velocity， deformation， breakup， splash， and rebound of supercooled large droplets. The multiple reference frame method is employed to deal with the fluid flow and heat transfer under the rotating condition. A three-dimensional numerical simulation is conducted to investigate the droplet impingement and ice accretion characteristics of entry components， including the inlet lip， spinner， and fan blades. The simulation results at rotational speeds of 0， 2 000， and 4 100 r/min show that the ice accretion on the inlet lip moves towards the outer surface of the inlet lip from the inner surface as the rotational speed increases. Moreover， the ice accretion on the blades is mainly concentrated at the blade root， and the ice accumulation decreases with the increase of rotational speed. The ice thickness on the inlet lip and spinner increases with increased rotational speed. The maximum ice thickness on the inlet lip and spinner under the rotational speed of 4 100 r/min increases by 0.27 and 2.46 times， respectively， compared to the stationary condition. This work can serve as a reference for developing subsequent anti/de-icing technology.
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This work was supported by the National Natural Science Foundation of China （No.51902256） and the Aeronautical Science Foundation of China （No.2020Z057053002）.
Clc Number:
V231.1
CHINA AERO-SCIENCES
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