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针对高超声速进气道的不起动振荡现象,提出了一种基于滑动多缝板的进气道不起动振荡控制概念,并对相关控制方案以及流动机理开展了风洞实验研究。实验中采用高速纹影技术和动态压力测量技术对整个控制过程中的瞬态流动结构和壁面动态压力信号特征进行了记录。结果表明:无论是在喉道后的唇罩上还是喉道前的压缩面上设置多缝板,均可在进气道不起动时通过泄流平衡进气道进出口流量差,进而达到抑制振荡的目的;随着多缝板的开启,进气道内的压力振荡幅度均不断减小,但是振荡频率的变化却并不相同,相较唇罩开缝方案中的频率保持不变,压缩面开缝方案中的振荡频率将随着通道内亚声速区的不断增大而升高;此外,压缩面开缝方案相较唇罩开缝方案能够对不起动过程中产生的分离包卸除,因而能够增强进气道的再起动能力。
Aiming at the phenomenon of non-starting oscillation of the hypersonic inlet, a concept of inlet non-starting oscillation based on sliding multi-slit plate was proposed. Wind tunnel experiments were carried out for the related control schemes and flow mechanism. High speed profiling and dynamic pressure measurement were used in the experiment to record transient flow structure and dynamic pressure signal characteristics of the wall. The results show that both the lamella behind the throat and the multi-slit plate on the compression surface in front of the throat can balance the inlet and outlet flow difference of the air inlet through the bleed when the air intake does not start, Oscillation; the pressure oscillation amplitude in the inlet decreases continuously with the opening of the multi-slit plate, but the oscillation frequency changes not the same as the frequency in the slotted lip slit, the compression surface The frequency of oscillation in the slotting scheme will increase with the increase of the subsonic sound velocity in the channel. In addition, the slotting scheme of the compression plane can remove the separation packets generated during the non-activation process compared with the lip slotting scheme Able to enhance the restart of the intake port.