内并联型TBCC进气道方案设计及验证  

Design and validation of scheme of over/under TBCC inlet

作　　者：张华军[1,2] 郭荣伟[1] 谢旅荣[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国人民解放军驻四二O厂军事代表室,成都610503

出　　处：《航空动力学报》2012年第11期2475-2483,共9页Journal of Aerospace Power

基　　金：国家高技术研究发展计划(2009AA7050303)

摘　　要：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<Ma0≤4.5时,进气道的总压恢复系数均在0.3以上,符合进气道总体方案的要求;冲压模态下,冲压通道的出口马赫数均小于0.4,出口静压均大于0.5个标准大气压,均能满足冲压燃烧室的燃烧需求.风洞试验结果表明:模态转换过程中,进气道涡轮通道具有良好的进/发匹配特性,且进气道涡轮/冲压通道具有良好的相容性能.研究结果可为我国开展组合动力研究提供方案参考和技术储备.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 ex- periment, 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 re- covery 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 at- mosphere 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.

关 键 词：组合发动机 内并联布局 进气道 泄流腔 数值模拟 风洞试验 

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]