非传统激波封口设计在高超声速进气道中应用可行性研究

推进技术 ›› 2015, Vol. 36 ›› Issue (7): 976-981.

非传统激波封口设计在高超声速进气道中应用可行性研究

黄思源

中国空气动力研究与发展中心超高速所高超声速冲压发动机技术重点实验室，四川绵阳 621000

发布日期:2021-08-15
作者简介:黄思源(1981—)，男，博士，副研究员，研究领域为湍流模式与燃烧。

Feasibility of Applying a Non-Traditional Shock-on-Lip Design to Hypersonic Inlet

Science and Technology on Scramjet Laboratory，China Aerodynamics Research and Development Center Hypersonic Institute，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 在马赫数4，5，6条件下借助轴对称数值模拟对4个高超声速轴对称进气道性能，即传统激波封口进气道、非传统激波封口进气道、改进非传统激波封口进气道和弯曲激波进气道，进行了比较研究。传统激波封口设计要求进气道各道外压缩激波在设计状态一起交于唇口，非传统激波封口设计要求各道外压缩激波分别在不同马赫数下交于唇口。结果表明:与传统激波封口进气道相比，非传统激波封口进气道在非设计状态的流量系数明显更高但在设计状态的总压恢复系数偏低；合理地改进设计能够减少非传统激波封口设计造成的总压损失。

关键词: 高超声速轴对称进气道；波系配置；可行性

Abstract: Performance of four hypersonic triple-cone inlets，namely，a traditional shock-on-lip inlet，a non-traditional shock-on-lip inlet，an improved non-traditional shock-on-lip inlet and a curved shock inlet，was investigated by axisymmetric numerical simulation at Mach number 4，5，6，respectively. The non-traditional shock-on-lip design requires the shock waves of an inlet to meet the cowl lip respectively at different Mach numbers，which is different from the traditional shock-on-lip design that requires external compression shock waves to meet the cowl lip together at the design condition. Results show，compared with the traditional shock-on-lip inlet，the non-traditional shock-on-lip inlet delivers obviously higher flow rate coefficient at off-design conditions but lower total pressure recovery coefficient at design condition. Proper improvement design can reduce the total pressure loss caused by the non-traditional shock-on-lip inlet design.

Key words: Hypersonic axisymmetric inlet；Shocks arrangement；Feasibility

黄思源. 非传统激波封口设计在高超声速进气道中应用可行性研究[J]. 推进技术, 2015, 36(7): 976-981.

HUANG Si-yuan. Feasibility of Applying a Non-Traditional Shock-on-Lip Design to Hypersonic Inlet[J]. Journal of Propulsion Technology, 2015, 36(7): 976-981.

参考文献

[1] Curran E T. Scramjet Engines: The First Forty Years [J].Journal of Propulsion and Power, 2001, 17(6): 1138-1148.
[2] Pearson L W. Hypersonic Research Engine Project. Phase 2A: Inlet Program [R]. NASA-CR-66797.
[3] Waltrup P J, White M E, Zarlingo F, et al. History of Ramjet and Scramjet Propulsion Development for U.S. Navy Missiles [J]. Johns Hopkins APL Technical Digest,1997, 18(2): 234-243.
[4] Colville J R, Starkey R P, Lewis M J. Extending the Flight Mach Number of the SR-71 Inlet[R]. AIAA 2005-3284.
[5] Mcclinton C, Roudakov A, Semenov V, et al. Comparative Flow Path Analysis and Design Assessment of an Axisymmetric Hydrogen Fueled Scramjet Flight Test Engine at a Mach Number of 6.5 [R]. AIAA 96-4571.
[6] Mahoney J J. Inlets for Supersonic Missiles [M]. Washington: American Institute of Aeronautics and Astronatics, 1990.
[7] Chyu W J, Kawamura T, Bencze D P. Navier–Stokes Solutions for Mixed Compression Axisymmetric Inlet Flow with Terminal Shock [J]. Journal of Propulsion and Power, 1989, 5(1): 4-5.
[8] Jesse R C, Ryan P S, Mark J L. Axisymmetric Inlet Design for Combined-Cycle Engines [J]. Journal of Propulsion and Power, 2006, 22(5): 1049-1058.
[9] Fan X Q, Li H, Jia D, et al. Experimental Investigation on Forced Boundary-Layer Transition of Axisymmetric Inlet and Numerical Verification [J]. Journal of Aircraft, 2006, 43(5): 1544-1549.
[10] Wang Y W, Sislian J P. Numerical Simulation of Gaseous Hydrocarbon Fuel Injection in a Hypersonic Inlet [J]. Journal of Propulsion and Power, 2010, 26(5): 1114-1124.
[11] Hyoung J L, Bok J L. Flow Characteristics of Small-Sized Supersonic Inlets [J]. Journal of Propulsion and Power, 2011, 27(2): 306-318.
[12] 郭善广, 柳军, 金亮, 等.吸气式高超声速推进助推段内流振荡及其抑制[J].推进技术, 2012, 33(1):20-25.(GUO Shan-guang, LIU Jun, JIN Liang, et al.Internal Flow Oscillations and Its Suppression for the Airbreathing Hypersonic Propulsion in Booster Stage [J].Journal of Propulsion Technology, 2002, 33(1):20-25.)
[13] Seddon J, Goldsmith E L. Intake Aerodanamics [M]. London: Blackwell Science, 1999:136-145.
[14] 骆晓臣, 周长省, 鞠玉涛. 提高固定几何二元进气道低马赫数性能的仿真研究[J].推进技术, 2010, 31(4).(LUO Xiao-chen, ZHOU Chang-sheng, JU Yu-tao.Numerical Investigation on Performance Improvement of Two-Dimensional, Fixed-Geometry Inlet at Low Mach Numbers[J]. Journal of Propulsion Technology, 2010, 31(4).)
[15] 向有志, 张堃元, 王磊, 等. 壁面压升可控的高超轴对称进气道优化设计[J].航空动力学报, 2011, 26(10):2193-2199.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-04-26；修订日期:2014-07-11。作者简介:黄思源(1981—),男,博士,副研究员,研究领域为湍流模式与燃烧。E-mail:huangsiyuan@tsinghua.org.cn