NASA组合发动机模态转换技术研究

Research on NASA Combined Cycle Engine Mode Transition

对NASA TBCC模态转换技术研究背景、存在的问题、模态转换试验与仿真情况进行了跟踪,研究表明模态转换过程要求维持推力性能不减小,几何调节、放气是进气道满足性能需求的关键,进气道与发动机相容性为研究重点,大尺度风洞试验是主要研究手段。试验与仿真结果验证了在飞行马赫数、飞行高度不变的情况下,维持推力性能不减小,进气道不发生不启动,推进系统由涡轮工作模态切换为双模态超燃冲压工作模态的可行性。

A systematic review on the background,key issues,experiment and simulation of NASA combined cycle engine mode transition is introduced. During the process of the mode transition from turbine engine to dual mode scramjet,the thrust of TBCC propulsion system must remain constant or increase.The variable and bleed inlet are the important approach to meet the thrust. The inlet engine compatibility is the research key of TBCC mode transition. The large scale wind tunnel experiment is one of the research means and tools. The results of experiment and simulation show that the vehicle Mach number and altitude are assumed to remain constant throughout the mode transition event,it is feasible for the thrust to remain constant or to increase without unstarting the inlet.