某型直升机发动机进气道热气防冰性能研究

Study on Performance of a Helicopter Engine Inlet Hot-air Anti-icing System

主要通过数值仿真和试验验证的方法对某型直升机发动机进气道热气防冰性能进行研究,在进气道水滴撞击特性数值计算的基础上,对其进行热力计算,确定结冰区域及表面温度分布。为验证数值仿真的准确性,针对不同外部工况条件设计了进气道热气防冰热性能试验,得到各试验测点在不同引气流量、温度、压力下的表面温度分布规律。试验分析结果表明,进气道温度分布最低区域与数值仿真结冰区域基本吻合,可保证所设计的热气防冰系统表面温度在防冰温度允许范围内,满足防冰要求,保障直升机飞行安全。

The performance of a helicopter engine inlet hot-air anti-icing system was studied by both of numerical method and experimental method. Based on the calculation of trajectories of the water droplets,numerical results of the icing area and the surface temperature distribution were presented. In order to verify the accuracy of numerical simulation,the anti-icing tests for different operating states were carried out,and the temperature distribution of various flow,temperature and pressure of air intake were obtained. The results showed that the numerical calculation of icing area was consistent with the experimental result on the whole,and the hot-air anti-icing system met the design requirements.