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为了在超燃冲压发动机直连式试验台上得到真实的非均匀试验气流,采用商业软件Fluent对高超声速流动的气体吹除控制进行了数值研究。在试验台喷管和发动机隔离段之间增加了吹除控制段,试验了4种吹除方案。常温空气从位于控制段顶部、侧部和底部的吹除口注入,吹除口包括长槽、短槽和圆孔等,吹除气体的流量为来流流量的8.3%~13.3%。以超燃冲压发动机自由射流计算结果为基准,比较分析了控制段出口截面马赫数分布。结果表明,“顶槽”方案能够得到较为理想的吹除效果,吹除参数优化后可为试验提供指导。
In order to obtain a real non-uniform test gas flow on a scramjet engine direct-coupled test rig, commercial software Fluent was used to numerically study gas blowing control at hypersonic flow. The blow-off control section was added between the test-bed nozzle and the engine isolation section and four blow-off scenarios were tested. Room temperature air is injected into the blow-off ports located at the top, the side and the bottom of the control section. The blow-off ports include long grooves, short grooves and round holes. The flow rate of the blow-off gas is 8.3% to 13.3% of the incoming flow. Based on the calculation results of the free jet of scramjet engine, the Mach number distribution at the exit section of the control section is comparatively analyzed. The results show that the “top tank” scheme can get a better blow-off effect, and the optimization of blow-off parameters can provide guidance for the experiment.