Restart control in two-dimensional twin-duct supersonic inlet through rotating cowl
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摘要:
针对双侧二元超声速进气道在非对称来流条件下的不起动现象，通过旋转背风侧/迎风侧唇罩进行了进气道再起动控制研究。采用非定常数值仿真方法，获得了几何壅塞背压加载方式下进气道的不起动流场，进而对比分析了旋转背风侧/迎风侧进气道唇罩的再起动过程。研究结果表明：随着几何壅塞程度加剧，进气道呈现出非对称工作状态，即背风侧进入深度不起动状态，而迎风侧表现为起动状态；在几何壅塞引发进气道不起动后，迎风侧唇罩不动，只旋转背风侧唇罩，该进气道无法恢复起动状态，其根本原因在于迎风侧出口气流对背风侧进气道的堵塞程度过大；而背风侧唇罩不动，只通过旋转迎风侧进气道唇罩使迎风侧捕获流量减小，可以有效缓解其对背风侧的堵塞，从而实现背风侧进气道再起动。
Abstract:An investigation into restart control strategies for a two-dimensional twin-duct supersonic inlet under asymmetric incoming flow conditions was conducted. The cowl was rotated on the windward and leeward sides to evaluate the efficacy in mitigating unstart. Unsteady numerical simulations were employed to capture the inlet’s unstart flow field under plug throttling-induced backpressure loading. The restart processes initiated by rotating the leeward-side and windward-side cowls were comparatively analyzed. The findings revealed that progressive plug throttling induced asymmetric inlet operation, characterized by a deep unstart condition in the leeward inlet, while the windward inlet maintained a started state. Following plug-throttling-induced unstart, leeward cowl rotation failed to achieve leeward inlet restart. This failure was attributed fundamentally to excessive flow blockage resulting from the predominance of windward outlet flow. In contrast, windward cowl rotation reduced its captured mass flow, effectively mitigating the blockage effects imposed on the leeward side and thereby facilitating successful restart of the leeward inlet.
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图 1 双侧二元进气道/补燃室一体化模型
Figure 1. Integrated model of two-dimensional twin-duct inlet and the afterburning chamber
图 6 不同网格量下背风侧进气道流量系数随时间变化曲线
Figure 6. Mass flow coefficient of the leeward inlet versus time under different mesh densities
图 7 不同时间步长下背风侧进气道流量系数随时间变化曲线
Figure 7. Mass flow coefficient of the leeward inlet versus time under different time steps
图 8 堵锥节流下背风侧进气道接近临界状态时马赫数分布
Figure 8. Mach number contour of the leeward inlet near the critical state under plug throttling
图 9 背风侧进气道不起动过程中背风侧/迎风侧进气道喉部流量系数随时间变化曲线
Figure 9. Mass flow coefficient of the leeward/windward inlet throat versus time during unstart of the leeward inlet
图 10 背风侧进气道不起动过程中背风侧进气道出口背压随时间变化曲线
Figure 10. Leeward exit back pressure versus time during unstart of the leeward inlet
图 11 背风侧进气道不起动过程中典型时刻马赫数分布（不起动锥位，θR=0°）
Figure 11. Mach number contours at typical instants during the leeward inlet unstart process （fixed plug，θR=0°）
图 12 背风侧进气道唇罩旋转期间进气道喉部流量系数随时间变化曲线
Figure 12. Mass flow coefficient of the inlet throat versus time during leeward cowl rotation
图 13 背风侧进气道唇罩旋转期间背风侧进气道出口背压随时间变化曲线
Figure 13. Leeward exit back pressure versus time during leeward cowl rotation
图 15 迎风侧进气道唇罩旋转期间进气道喉部流量系数随时间变化曲线
Figure 15. Mass flow coefficient of the inlet throat versus time during windward cowl rotation
图 16 迎风侧进气道唇罩旋转期间背风侧进气道出口背压随时间变化曲线
Figure 16. Leeward exit back pressure versus time during windward cowl rotation
图 17 大幅振荡期间进气道性能随时间变化曲线
Figure 17. Inlet performance variation during violent oscillations
图 18 旋转迎风侧进气道唇罩大幅振荡期间马赫数分布
Figure 18. Mach number contours during violent oscillations of rotating windward cowl
图 19 小幅振荡期间进气道性能随时间变化曲线
Figure 19. Inlet performance variation during minor oscillations
图 20 旋转迎风侧进气道唇罩小幅振荡期间马赫数分布
Figure 20. Mach number contours during minor oscillations of rotating windward cowl
图 21 旋转迎风侧进气道唇罩再起动过程中马赫数分布
Figure 21. Mach number contours during restart process of windward inlet with rotating cowl
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