一种外并联型涡轮基组合循环发动机进气系统方案

提出了一种外并联型涡轮基组合循环发动机可变几何进气道气动设计方案.数值模拟研究了该变几何方案沿飞行轨迹的气动性能参数变化.在此基础上,对设计参数和进气道几何调节规律进行研究,得到了较优的进气道调节规律及典型工作点进气道气动性能.结果显示:不同来流马赫数下,涡轮通道喉道截面总压恢复系数不低于0.69,冲压通道出口截面总压恢复系数在0.38以上. 

Over/under type inlet scheme for turbine-based combined cycle engine

A design scheme of variable geometry over/under type inlet for turbine-based combined cycle engine was presented.Numerical simulation was carried out to investigate the variation of aerodynamic performance of this variable geometry inlet scheme along flight envelop.On basis of this,the design parameters and geometry modulating law were studied.A superior operating law was acquired.The inlet performance of typical work point was provided.Results indicate that the total pressure recovery coefficients at throat section of turbine inlet and exit section of scramjet inlet are not less than 0.69 and 0.38 under different freestream Mach number.