抽吸对方转圆内收缩进气道性能的影响

发布时间：2018-05-05 06:10

本文选题：内收缩进气道 + 抽吸　；参考：《航空学报》2016年12期

【摘要】：针对马赫数可控的方转圆内收缩进气道设计了抽吸方案,并通过风洞试验和数值仿真手段研究了其对进气道性能的影响,获得了进气道设计点的工作特性及自起动性能。试验结果验证了抽吸对提升内收缩进气道性能的有效性:在顶板下洗气流集中区域开槽减小了出口涡流区以及提高了抗反压能力,相对原型进气道,设计点(Ma=6.0)放气流量为0.99%的实际捕获流量时出口总压恢复系数提高了3.8%,临界反压从135倍来流静压提高到了150倍。此外,在顶板分离区开槽可以提高进气道的自起动能力,Ma=5.0,攻角AOA=4°时实现了自起动,此时放气流量为0.78%的进口捕获流量,起动后出口增压比和总压恢复系数分别为30.6和0.600。
[Abstract]:A suction scheme is designed for the inlet air inlet with a controlled Maher number, and the effect on the inlet performance is studied by wind tunnel test and numerical simulation. The working characteristics and self starting performance of the inlet design point are obtained. The experimental results verify the effectiveness of suction on the performance of the inlet in the lift inlet. The flow field in the down flow concentration area reduces the outlet swirl zone and improves the anti pressure ability. Relative to the prototype intake port, the total pressure recovery coefficient of the outlet pressure is increased by 3.8% when the design point (Ma=6.0) discharge flow is 0.99%, and the critical back pressure increases from 135 times to 150 times. In addition, the slotting in the roof separation area can be raised. The self starting capacity of the high intake port, Ma=5.0 and the angle of attack AOA=4 degree, the self starting, at this time the discharge flow is 0.78%, the inlet pressure ratio and the total pressure recovery coefficient after starting are 30.6 and 0.600., respectively.

【作者单位】：南京航空航天大学能源与动力学院;中国航天科技集团公司西安航天动力研究所;中国航天科技集团公司西安航天动力技术研究所;
【基金】：国家自然科学基金(90916029,91116001)~~
【分类号】：V211.48

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