某航空发动机短舱防冰腔流动与换热仿真

Simulation of a Short-cabin Anti-ice Chamber Flow and Heat Exchange of an Aero-engine

本文以发动机唇口的热气防冰为研究对象,建立了三维模型,通过对不同引气速度、引气温度下防冰腔内流动及传热的计算,定量分析了上述参数对防冰有效性的影响。通过研究发现,引气速度从10 m/s增加至40 m/s,防冰表面最低温度由266.4 K升至286.2 K;而当引气温度从100℃增加到130℃时,防冰表面最低温度则由286.2 K升至307.1 K。因此当引气速度不低于15 m/s、来流温度不低于380 K时,可以实现短舱唇口的有效防冰。

This study focuses on the thermal anti-icing of the engine nacelle inlet lip.A three-dimensional model was established to quantitatively analyze the effects of different bleed air velocities and temperatures on the flow and heat transfer within the anti-icing cavity.By conducting calculations,it was found that increasing the bleed air velocity from 10 m/s to 40 m/s resulted in a decrease in the minimum temperature on the anti-icing surface from 266.4 K to 286.2 K.Similarly,increasing the bleed air temperature from 100℃to 130℃raised the minimum temperature on the anti-icing surface from 286.2 K to 307.1 K.Therefore,effective anti-icing of the engine nacelle inlet lip can be achieved when the bleed air velocity is not lower than 15 m/s and the incoming flow temperature is not lower than 380 K.