基于主动射流控制的二元混压式进气道起动特性研究

Study on starting characteristics of a two-dimensional supersonic inlet based on active injection control

以N-S时均化方程为控制方程,采用SSTk-ω湍流模型对主动射流控制下的典型二元混压式超声速进气道二维定常流场进行了数值模拟和分析,验证了利用主动射流控制改善进气道起动特性的可行性,研究了不同射流流量、速度、总温对进气道起动特性的影响。结果表明,发现射流冲量大小是利用主动射流实现进气道迟滞回路内再起动的关键因素,当射流冲量大于某一阈值后,进气道即能实现再起动。研究还发现,采用主动射流控制技术后,进气道基本能消除迟滞回路现象。

The steady flow in a typical two-dimensional mixed-compression supersonic inlet was simulated and analyzed with time-average N-S equations and SST k-ψ turbulence modeling.The feasibility of active injection control was validated to improve starting characteristics of the inlet.Influence of injection with different flow rate,velocity and total temperature on starting characteristics of the inlet was studied.The results show that injection impulse is the key factor on inlet restart in the hysteresis,and the inlet can be restarted when the injection impulse exceeds the threshold.The results also show that the phenomenon of the hysteresis can be eliminated basically with active injection control.