微引射式防冰腔结构参数对换热性能的影响

Influence of Structural Parameters of Micro-ejection Anti-icing Cavity on Hot Air Anti-icing Performance

采用数值模拟的方法研究了航空发动机微引射式防冰腔结构参数对防冰热效率和发动机蒙皮温度分布的影响。通过改变射流孔直径、射流孔孔距、混合腔长径比和波纹板通道出口高度,建立了不同的微引射式防冰腔模型。在进口热气流量一致的情况下,对不同防冰腔模型进行了数值计算。结果表明:减小射流孔直径和波纹板通道出口截面高度能提高防冰热效率和蒙皮表面平均温度;射流孔孔距和混合腔长径比存在一个最优值使防冰腔换热性能最好。

Numerical simulation methods are applied to research the influence of structural parameters of micro-ejection anti-icing cavity of aircraft engine on thermal efficiency and surface temperature distribution.By changing jet hole diameter,jet hole spacing,mixing chamber aspect ratio and the height of variable cross-section corrugated sheet,different micro-ejection anti-icing cavity models are established.With the same inlet hot air flow,numerical simulations are carried out on different anti-icing cavity models.The results show that reducing the diameter of jet hole and the height of exit section of corrugated sheet channel can improve the anti-icing thermal efficiency and the average temperature of the skin,and there is an optimal value for jet hole spacing and length-diameter ratio of mixing chamber to make anti-icing cavity the best heat transfer performance.