一型逆时针主旋翼的双发直升机进气流场数值仿真分析  

Numerical simulation analysis of inlet flow field of anti-clockwise main rotor helicopter with two engines

作　　者：杨柳 刘雨 YANG Liu;LIU Yu(Chinese Flight Test Establishment,Aviation Industry Corporation of China,Limited,Xi’an 710089,China)

机构地区：[1]中国航空工业集团有限公司中国飞行试验研究院,西安710089

出　　处：《航空动力学报》2024年第6期207-215,共9页Journal of Aerospace Power

摘　　要：通过数值仿真方法模拟了一型逆时针主旋翼的双发直升机在稳定前飞、侧飞、悬停状态下的流场,获取了不同飞行状态下的进气总压损失和进气温升。结果显示:稳定前飞时发动机进气面平均总压损失随飞行速度增大而增大,最大约为1.61%;侧飞时下游发动机进气道外侧区域存在较大的进气总压损失,且下游发动机进气存在较大温升;同速度下右侧飞时下游发动机进气温升幅度更高,对发动机工作性能影响更大;悬停状态下发动机进气面平均总压损失最大约为1.14%。通过与该型直升机飞行数据对比,验证了数值仿真结果的有效性。研究结果可以为国内同类型直升机试飞科目规划和发动机安装损失评估提供参考。The flow field of an anti-clockwise main rotor helicopter with two engines in steady forward flight,side flight and hovering was simulated by numerical simulation method,and the total inlet pressure loss and inlet temperature rise under different flight states were obtained.The results showed that the average total pressure loss of the engine intake surface increased with the increase of steady forward flight speed,and the maximum was about 1.61%.During side flight,there was a large total pressure loss in the outer area of the downstream engine inlet and a large air temperature rise in the downstream engine inlet.At the same speed,the inlet temperature rise of the downstream engine was higher when flying on the right wind,which had greater influence on the engine performance.The maximum average total pressure loss of the engine inlet surface was about 1.14%under the hovering state.Compared with the flight data of this helicopter,the effectiveness of the numerical simulation results was verified.The result can provide a reference for domestic flight test subject planning and engine installation loss evaluation of the same type of helicopter.

关 键 词：直升机 稳定前飞 侧飞 悬停 进气总压损失 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]