一种改善高超声速进气道自起动能力的流场控制研究

doi:10.7527/S1000-6893.2014.0125

流体力学与飞行力学

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一种改善高超声速进气道自起动能力的流场控制研究

王建勇¹, 谢旅荣^1,2, 赵昊¹, 滕瑜琳¹

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191

收稿日期:2014-04-18 修回日期:2014-06-23 出版日期:2015-05-15 发布日期:2014-09-16
通讯作者: 谢旅荣Tel.: 025-84892200-2415 E-mail: xielvrong@nuaa.edu.cn E-mail:xielvrong@nuaa.edu.cn
作者简介:王建勇男, 硕士研究生。主要研究方向: 内流气体动力学。 E-mail: dreamwjyong@163.com谢旅荣女, 博士, 副教授, 硕士生导师。主要研究方向: 内流气体动力学。 Tel: 025-84892200-2415 E-mail: xielvrong@nuaa.edu.cn;赵昊男, 硕士研究生。主要研究方向: 内流气体动力学。 E-mail: huang@nuaa.edu.cn;滕瑜琳男, 硕士研究生。主要研究方向: 内流气体动力学。 E-mail: t_yl1991@163.com
基金资助:
国家自然科学基金 (11302101);南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20130203);中央高校基本科研业务费专项资金

A flow-control conception of improving self-start performance of hypersonic inlet

WANG Jianyong¹, XIE Lyurong^1,2, ZHAO Hao¹, TENG Yulin¹

1. Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

Received:2014-04-18 Revised:2014-06-23 Online:2015-05-15 Published:2014-09-16
Supported by:
National Natural Science Foundation of China (11302101); the Foundation of Graduate Innovation Center in NUAA (kfjj20130203); the Fundamental Research Funds for the Central Universities

摘要/Abstract

摘要：

为了改善高超声速进气道在低马赫数下的自起动能力,提出了一种在进气道内利用不起动时诱导激波前后静压差开设回流通道的流场控制概念,对其改善流场特性的机理及回流通道典型几何参数对进气道流场特性和气动性能的影响进行了分析,获得了回流通道典型几何参数对进气道自起动性能的影响规律,并与原型面进气道性能进行对比分析。结果表明:回流通道使进气道自起动马赫数由Ma=4.7降低至Ma=3.6,进气道工作马赫数范围得到显著拓宽;回流通道进口位置对进气道自起动马赫数存在较大影响,但自起动马赫数几乎不随回流通道出口位置、回流通道宽度(b≥8 mm)而改变;在低马赫数时,回流通道对进气道不起动流场有明显改善。而高马赫数下回流通道对进气道性能几乎不产生影响,保证了高马赫数下进气道的性能。

关键词: 高超声速进气道, 回流通道, 几何参数, 自起动马赫数, 进气道性能

Abstract:

To improve the self-start performance of hypersonic inlet at low Mach number, a flow-control conception of backflow duct is put forward, which is driven by the pressure difference generated by the separation induced shock under unstart conditions. The influencing principles are analyzed, and the characteristics of inlet's flow field and the inlet's aerodynamic performances affected by variable geometry parameters of the backflow duct are investigated. Finally, compared with the primary inlet's performances, the results indicate that due to the backflow duct, the self-start Mach number is ascended from Ma=4.7 to Ma=3.6, expending the operating Mach range remarkably. The location of the backflow duct's entrance influences the self-start performance significantly, while the location of backflow duct's exit and the width of backflow duct's section (b≥8 mm)scarcely affectes the self-start ability. At low Mach number, the unstarted flow field of inlet is improved by the backflow duct considerably.But at high Mach number, the influence of backflow duct would be slight, satisfying the design performance requirements.

Key words: hypersonic inlet, backflow duct, geometry parameters, self-start Mach number, inlet performances

中图分类号:

V231.3

王建勇, 谢旅荣, 赵昊, 滕瑜琳. 一种改善高超声速进气道自起动能力的流场控制研究[J]. 航空学报, 2015, 36(5): 1401-1410.

WANG Jianyong, XIE Lyurong, ZHAO Hao, TENG Yulin. A flow-control conception of improving self-start performance of hypersonic inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(5): 1401-1410.

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E-mail：hkxb@buaa.edu.cn

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一种改善高超声速进气道自起动能力的流场控制研究

A flow-control conception of improving self-start performance of hypersonic inlet

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