基于合成射流的机翼溢流冰防护实验

为了解决电加热防/除过程中,机翼前缘溢流水流至防护区后侧形成冰脊影响飞行安全的问题,提出一种电加热系统与合成射流激励器复合式防冰方法。该方法将电加热系统布置于机翼前缘,通过加热使得机翼前缘温度高于冻结温度,防止过冷水滴在机翼前缘冻结,合成射流出口位于电加热系统防护区下游,通过合成射流的吹吸作用改变溢流水的运动轨迹,防止前缘溢流水流至机翼后表面形成冰脊。在结冰风洞中,通过实验研究了液态水含量、环境温度和合成射流速度对电加热与合成射流复合式防冰性能的影响。实验结果表明:电加热与合成射流复合式防冰系统在设计的结冰气象条件下,不仅能够保持机翼前缘不结冰,还能消除机翼后表面的冰脊。

Experiment on airfoil runback ice protection based on synthetic jet,

A hybrid ice protection method combining thermoelectric systems and synthetic jet actuators was designed to solve the problem of runback ice. In this method, the thermoelectric system was arranged on the leading edge of the wing to prevent the supercooled water droplets from freezing. The synthetic jet slot was located downstream the thermoelectric system to change the trajectory of runback water. The effects of the liquid water content, the incoming flow and the velocity of synthetic jet on the anti-icing performance of the hybrid ice protection system were studied in the icing wind tunnel. The results showed that the hybrid ice protection method could keep both the leading-edge and downstream regions free from icing.