抽吸对方转圆内收缩进气道性能的影响

doi:10.7527/S1000-6893.2016.0065

流体力学与飞行力学

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抽吸对方转圆内收缩进气道性能的影响

李永洲^1,2, 张堃元¹, 孙迪³

1. 南京航空航天大学能源与动力学院, 南京 210016;
2. 中国航天科技集团公司西安航天动力研究所, 西安 710100;
3. 中国航天科技集团公司西安航天动力技术研究所, 西安 710025

收稿日期:2015-12-24 修回日期:2016-03-04 出版日期:2016-12-15 发布日期:2016-03-08
通讯作者: 李永洲,Tel.:029-85208061,E-mail:nuaa-2004@126.com E-mail:nuaa-2004@126.com
作者简介:李永洲,男,博士,工程师。主要研究方向:高超声速推进技术和内流气体动力学。Tel.:029-85208061,E-mail:nuaa-2004@126.com;张堃元,男,教授,博士生导师。主要研究方向:高超声速推进技术和内流气体动力学。Tel.:025-84892201-2100,E-mail:zkype@nuaa.edu.cn;孙迪,女,硕士,工程师。主要研究方向:高超声速气动热力学。Tel.:029-85208061,E-mail:sinda.y@163.com
基金资助:
国家自然科学基金（90916029，91116001）

Effect of suction on performance of inward turning inlet with rectangular-to-circular shape transition

LI Yongzhou^1,2, ZHANG Kunyuan¹, SUN Di³

1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China;
3. Xi'an Institute of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Xi'an 710025, China

Received:2015-12-24 Revised:2016-03-04 Online:2016-12-15 Published:2016-03-08
Supported by:
National Natural Science Foundation of China (90916029, 91116001)

摘要/Abstract

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。

关键词: 内收缩进气道, 抽吸, 风洞试验, 起动性能, 涡流区

Abstract:

Various suction schemes are designed for an inward turning inlet with rectangular-to-circular shape transition with controlled Mach number distribution. Experiments and numerical simulations are conducted to analyze the influence of the scheme on the performance of the inlet. The operation characteristics of the design point and the self-starting performance are obtained. The experimental results validate that suction can efficiently improve the performance of the inlet. The bleeding in the downwash concentration region of the top wall can obviously reduce the exit vortex region and improve the back pressure resistance. Compared with those of the original inlet, the total pressure recovery coefficient increases by 3.8% and the critical back pressure increases from 135 times of the free stream static pressure to 150 times at the exit section on the design point (Ma=6.0), when the relative bleeding flux is 0.99%. In addition, the bleeding in the separation region of the top wall can promote the starting ability. When Ma=5.0 and AOA=4°, the inlet realizes self-starting with the relative bleeding flux being 0.78%. When the inlet restarts, the corresponding compression ratio and the total pressure recovery coefficient at the exit section are 30.6 and 0.600, respectively.

Key words: inward turning inlet, suction, wind tunnel test, starting performance, vortex region

中图分类号:

V231.3

李永洲, 张堃元, 孙迪. 抽吸对方转圆内收缩进气道性能的影响[J]. 航空学报, 2016, 37(12): 3625-3633.

LI Yongzhou, ZHANG Kunyuan, SUN Di. Effect of suction on performance of inward turning inlet with rectangular-to-circular shape transition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3625-3633.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

抽吸对方转圆内收缩进气道性能的影响

Effect of suction on performance of inward turning inlet with rectangular-to-circular shape transition

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