螺旋桨滑流对涡轮螺旋桨进气道气动性能影响仿真研究  

Simulation on the influence of propeller slipstream on aerodynamic performance of turboprop inlet

作　　者：王伟杰 张宜琳 吴卓远 Wang Weijie;Zhang Yilin;Wu Zhuoyuan(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Jiangsu Nanjing,210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械设计与制造工程》2024年第11期75-79,共5页Machine Design and Manufacturing Engineering

摘　　要：基于计算流体动力学方法,对螺旋桨滑流对涡轮螺旋桨飞机发动机进气道性能的影响进行仿真分析。使用多重参考系方法模拟螺旋桨滑流效应,分别在设计状态点和非设计状态点下分析了有、无滑流对进气道主流道性能的影响。结果显示:设计状态点有滑流状态与无滑流状态相比,总压恢复系数和总压畸变指数均有增大,地面状态下总压恢复系数增大了约3%,总压畸变指数增大0.0823~0.0980;高空状态下总压恢复系数增大了约2%,总压畸变指数增大0.0737~0.1048。非设计状态点随来流马赫数的增大,总压恢复系数和总压畸变指数逐渐减小。Based on computational fluid dynamics methods,a simulation analysis is conducted on the influence of propeller slipstream on the inlet performance of turboprop aircraft engines.The multiple reference frame method is used to simulate the propeller slipstream effect,and the effects of the presence and absence of slipstream on the main flow performance of the inlet are analyzed at both design and non design state points.The results show that compared with the non slip state,the total pressure recovery coefficient and total pressure distortion index increase in the design state point with slip flow.The total pressure recovery coefficient increases by about 3% in the ground state,and the total pressure distortion index increases by 0.0823~0.0980;The total pressure recovery coefficient increases by about 2% in high-altitude conditions,and the total pressure distortion index increases by 0.0737~0.1048.As the Mach number of the incoming flow increases,the total pressure recovery coefficient and total pressure distortion index gradually decrease at non design state points.

关 键 词：涡轮螺旋桨进气道 螺旋桨滑流 总压恢复系数 总压畸变指数 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]