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采用自适应泄压控制技术解决宽范围定几何高超进气道低马赫数下自起动问题,利用数值仿真对一种采用自适应泄压控制的高性能二元高超进气道单个自适应泄压槽的位置、角度、有效流通面积等主要设计参数对泄漏量以及进气道总体性能的影响规律开展了研究.结果表明:泄压槽参数变化对基准进气道总体性能影响较小,总压恢复系数在2%范围内变化.位于唇口激波反射点下游的槽的泄漏量较大且随开槽角度的增加而减小,随有效流通面积的增加成线性增加;相同条件下,自适应泄压槽的泄漏量只有常规顺向放气槽的50%;随来流马赫数升高,自适应泄压槽的漏气量明显减小,高马赫数下接近气动自封闭状态.
The self-adaptive pressure relief control technology is used to solve the problem of self-starting under a wide range of geometric high-altitude inlet low Mach number. By using numerical simulation, a single self-adaptive pressure relief Slot position, angle, effective flow area and other major design parameters of the leakage and the overall performance of the intake duct carried out a study of the results show that: the pressure relief groove parameters of the baseline intake port overall performance of less impact, the total pressure The recovery coefficient changes within the range of 2% .The leakage of the groove located downstream of the lip reflection point of the lip is larger and decreases with the increase of the slot angle, and increases linearly with the increase of the effective flow area. Under the same conditions, The leakage rate to adapt to the pressure relief tank is only 50% of that of the conventional forward deflation tank. With the increase of the flow Mach number, the leakage of the adaptive pressure relief tank is obviously reduced, and the gas is close to the pneumatic self-closing state under the high Mach number.