论文部分内容阅读
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。
Mainly through the numerical simulation and experimental verification methods to study a certain type of helicopter engine inlet anti-icing performance of air in the inlet droplet impact on the basis of the numerical calculation of its thermal calculation, to determine the icing area and the surface temperature distributed. In order to verify the accuracy of the numerical simulation, the thermal performance of hot gas anti-icing inlets was designed according to different external working conditions, and the surface temperature distribution of each test point under different flow rates, temperatures and pressures was obtained. The experimental results show that the minimum inlet air temperature distribution agrees well with the numerical simulation freezing area, which can ensure that the surface temperature of the designed anti-ice system is within the allowable range of anti-icing temperature, meet the anti-icing requirements and ensure the helicopter flight safety.