内并联型TBCC进气道方案设计及验证

提出了一种带可变几何泄流腔的内并联型涡轮基组合循环(TBCC)进气道设计方案.介绍了进气道的总体设计思路,给出了进气道的设计马赫数、转级马赫数及飞行轨迹,对不同来流条件下进气道的工作方式以及全马赫数范围进气道型面调整的安排进行了论述,确定了进气道主要气动参数与型面参数的选取原则.通过数值模拟和高速风洞试验的手段,对进气道设计方案的可行性进行了验证.数值模拟结果表明:当Ma0≤2.5时,进气道的总压恢复系数均在0.8以上,当2.5

Design and validation of scheme of over/under TBCC inlet

Scheme of an over/under type TBCC inlet with variable geometry bleed cavity was presented.The general design methodology of the inlet was introduced and the design Mach number,transition Mach number and flight trajectory were provided.Discussion was conducted concerning the work mode of the inlet under different free stream conditions and the adjustment of the geometry shape of the inlet in the range of flight Mach number,based on which the major aerodynamic parameters and the selection principle of shape parameters were confirmed.Through methods of numerical simulation and high speed wind tunnel experiment,the feasibility of the scheme of the inlet was validated.The numerical simulation results indicate:when the free stream Mach number is less than 2.5,the total pressure recovery of the inlet is beyond 0.8.When the free stream Mach number is from 2.5 to 4.5,the total pressure recovery of the inlet is beyond 0.3.The aerodynamic characteristics of the inlet meet the demands of the scheme.At ramjet mode,the exit Mach number of the ramjet diffuser is below 0.4 and the exit pressure of the ramjet diffuser is beyond 0.5 standard atmosphere pressure.The ramjet diffuser can fulfil the combustion condition of the ramjet combustion chamber.The wind tunnel experiment results indicate:in mode transition,the turbojet diffuser has good matching characteristics with the engine and the turbojet/ramjet diffusers have good compatible characteristics.therefore it can be concluded that the scheme of the inlet is viable.Results of the research would provide scheme reference and technology storage for the combined cycle propulsion evolution in our country.