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以机翼热气防冰系统为研究对象,建立了包含热气防冰系统防冰腔内外流场对流换热和固体结构导热的三维稳态流-固耦合传热物理模型,对整个计算区域生成混合网格,边界条件为第三类边界条件,采用计算流体力学方法以FLUENT软件为工具,对干空气飞行状态下流-固耦合传热模型进行了求解,获得防冰腔蒙皮内外表面对流换热系数分布和温度场结果,并对计算结果进行了分析。结果表明:防冰腔铝合金蒙皮沿展向和厚度方向导热显著,温度分布较均匀,防冰引气温度为200℃时,防冰腔蒙皮内外表面上最高温度为101℃,最低温度为21℃,3mm厚的蒙皮同一点处内外表面最大温差仅为4℃,防冰腔排气口处气体的平均温度为63℃。热气防冰系统蒙皮温度场计算方法和计算结果,能够为热气防冰系统干空气飞行试验设计和测试中温度传感器的选型与布置提供依据。
Taking the wing air-ice anti-icing system as the research object, a three-dimensional steady-state fluid-solid coupling heat transfer physical model including convective heat transfer and solid-state heat transfer in and out of the anti-icing system is established. Mesh and boundary conditions are the third type of boundary conditions. Fluid-solid coupling heat transfer model under dry-air flight condition is solved by computational fluid dynamics method with FLUENT software to obtain the convective heat transfer on the inner and outer surfaces of the ice- Coefficient distribution and temperature field results, and the calculation results were analyzed. The results show that the anti-icing aluminum alloy skin has significant thermal conductivity in both the span and thickness directions and the uniform temperature distribution. When the anti-ice air temperature is 200 ℃, the maximum temperature on the inner and outer surfaces of the anti- For 21 ℃, 3mm thick skin at the same point the maximum temperature difference between the inner and outer surface is only 4 ℃, anti-ice chamber exhaust gas at an average temperature of 63 ℃. The calculation methods and calculation results of the skin temperature field of the anti-ice system can provide the basis for the selection and arrangement of the temperature sensors in the design and testing of the dry air flight test of the hot air anti-icing system.