摘要
采用逆向开槽技术,对三维内乘波式高超声速进气道的低马赫数起动和抗反压能力进行研究,提出了逆向直泄流槽和逆向倒角泄流槽两种方案。数值研究结果表明:逆向泄流槽在三维内乘波式进气道自起动和抗反压过程中起到气动开关作用。进气道不起动或反压过高时,泄流槽处于开启状态;进气道起动后,泄流槽接近气动关闭状态,对进气道总体性能影响较小。两种逆向泄流槽都拓宽了三维内乘波式进气道的低马赫数起动范围,提高了进气道的抗反压能力。其中,逆向倒角泄流槽比逆向直泄流槽具有更宽的低马赫数起动范围和更强的抗反压能力。
Two bleed-slot patterns were applied to the internal waverider-derived hypersonic inlet. Both of them consisted of two parallel slots and reverse to the incoming flow direction. The geometric shapes of the two slot patterns were similar except for the curved chamfer on the slot surface near the inlet wall. Numeri-cal simulations were carried out to examine the influence of bleeding systems on the inlet performance. The results show that reverse bleed slots behave independently on the inlet flow status. When the inlet is un-started or the back-pressure is too high, the bleeding slots are fully opened to receive more spillage. On the other hand, the slots are aerodynamically self-adapted to be closed once the inlet is started, which re-sults in a little effect on the inlet performance. Both straight and chamfered reverse bleed slots can lower the starting Mach number, and increase the back-pressure resistance of the internal waverider-derived hyper-sonic inlet. In particular, the chamfered slots have a better performance than the straight one regarding the capability of back-pressure resistance.
出处
《燃气涡轮试验与研究》
北大核心
2013年第6期40-45,34,共7页
Gas Turbine Experiment and Research
基金
国家自然科学基金(51006051)
关键词
逆向泄流槽
内乘波式进气道
自起动
抗反压
高超声速
数值模拟
reverse bleed slots
internal waverider-derived inlet
self-starting
back-pressure resistance
hypersonic
numerical simulation
