某型飞机发动机短舱防冰系统设计计算

Design and calculation of aircraft nacelle anti-icing system

介绍了某型飞机发动机短舱防冰系统的结构形式和防冰原理,按照可利用热量应大于所需热量的原则,通过计算完全蒸发和湿状态下的热载荷,确定了发动机短舱防冰严酷状态及所需热流量.基于机翼水收集系数和数据相似原则,利用欧拉法两相流计算方法,确定了短舱防冰系统水收集系数.按照在湿状态下允许有一定结冰量存在的设计原则,根据发动机的吞冰能力,利用VSAERO/ICE工具对发动机短舱防冰系统进行了计算,计算结果表明,在严酷状态下,防冰系统能够满足允许结冰厚度要求.

The structure and theory of engine nacelle anti-icing （NAI） system were in- troduced. According to the principle that the heat available should be larger than the heat required, the critical design point and required flows of NAI were determining by calculating the required bleed air at complete evaporation and running wet station respectively. The co- efficient of water collection of NAI system was determined using Euler method based on the coefficient of water collection of wing and the data similarity rule. According to the theory of allowed maximum thickness of ice, the performance of NAI system was calculated using the VSAERO/ICE software. The result of simulation shows that the maximum thickness of ice can meet at the critical condition.