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基于流固耦合传热的思想建立了一套飞机热气防冰系统的的数值模拟方法,并将其与积冰热力学模型结合起来,实现了热气防冰系统开启时的机翼积冰预测.采用格心格式有限体积法求解N-S方程获得防冰腔与外流场;通过欧拉法在外流场的基础上获得过冷水滴撞击特性;求解三维热传导偏微分方程获得蒙皮的传热特性;采用交接面插值的方法实现防冰腔到外流场的热量传递;建立了考虑三维溢流效应的积冰热力学模型并在此基础上开展了机翼冰脊的数值预测.数值模拟结果表明:热气防冰系统开启时加热机翼表面温度最高可达308K,加热区后的上下机翼表面均有冰脊形成,通过对结果的分析表明该方法是合理可行的.
Based on the idea of fluid-structure coupled heat transfer, a set of numerical simulation method of aircraft anti-ice system is established, which is combined with the thermodynamic model of ice accumulation to realize wing ice prediction when the anti-ice system is opened. The lattice-cavity finite volume method is used to solve the NS equation to obtain the anti-ice cavity and the outflow field. The over-cooled droplet impact property is obtained by the Euler method based on the outflow field. The heat transfer characteristic of the skin is obtained by solving the three-dimensional heat conduction partial differential equation. The method of interface interpolation is used to transfer the heat from the anti-ice chamber to the external flow field. The ice accumulation thermodynamic model considering the three-dimensional overflow effect is established and the numerical prediction of ice ridge is carried out. Numerical simulation results show that: When the anti-icing system is turned on, the surface temperature of the heating wing reaches up to 308K, and the ice ridge forms on the upper and lower wing surfaces after the heating zone. The analysis of the results shows that the method is reasonable and feasible.