隔板对低外阻二元高马赫数进气道反压特性的影响

推进技术 ›› 2019, Vol. 40 ›› Issue (3): 487-495.

隔板对低外阻二元高马赫数进气道反压特性的影响

吴中明¹,张德平²,王肖¹,谢文忠¹

南京航空航天大学能源与动力学院，江苏南京 210016,四川航天系统工程研究所，四川成都 610100,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016

发布日期:2021-08-15
作者简介:吴中明，硕士生，研究领域为内流气体动力学。E-mail: wzm0603@163.com 通讯作者:谢文忠，博士，副教授，研究领域为内流气体动力学。

Impact of Splitter on Back Pressure Characteristics of Low Cowl-Drag High Mach Number Inlets

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Sichuan Aerospace Institute of System Engineering，Chengdu 610100，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了提高低外阻二元高马赫数进气道的抗反压性能，研究了在内收缩段设置隔板对低外阻二元高马赫数进气道抗反压能力的影响，通过数值仿真计算了两组不同内收缩比的低外阻二元高马赫数进气道内收缩段有/无隔板下的反压特性，并对比分析了相应的流场结构。结果表明，隔板能够显著抑制低外阻二元高马赫数进气道内强激波/边界层干扰现象，改善隔离段入口截面气流参数分布的均匀性，使隔离段内激波串结构上下较为对称地推进。内收缩比1.566进气道引入隔板能够将极限反压提高4.2%。引入隔板能够在增加进气道压缩效率的前提下，提高进气道的最大抗反压能力，拓宽进气道的稳定工作范围。

关键词: 高马赫数进气道；隔板；低外阻；反压特性

Abstract: In order to improve the maximum back pressure of low-cowl drag two-dimensional high Mach number inlets，the impact of a splitter located in the internal contraction portion on the maximum back pressure of low-cowl drag two-dimensional high Mach number inlets was studied. Numerical simulations were conducted to study the back pressure characteristics of two groups of low cowl-drag two-dimensional high Mach number inlets with and without splitter. The corresponding flowfield structures were analyzed. Results show that，inserting a splitter in the internal contraction section can significantly suppress the severe shock wave/boundary layer interaction and improve the uniformity of airflow parameters distribution，so as to make the shock train propagate upstream sysmetrically. The maximum back pressure of ICR1.566 inlets can be increased by 4.2% by splitter. The splitter not only increases the compression efficiency，but also improves the maximum back pressure of low cowl-drag high Mach number inlets，which can widen the stable operation range of high Mach number inlets.

Key words: High Mach number inlet；Splitter；Low cowl-drag；Back pressure characteristics

吴中明,张德平,王肖,谢文忠. 隔板对低外阻二元高马赫数进气道反压特性的影响[J]. 推进技术, 2019, 40(3): 487-495.

WU Zhong-ming¹,ZHANG De-ping²,WANG Xiao¹,XIE Wen-zhong¹. Impact of Splitter on Back Pressure Characteristics of Low Cowl-Drag High Mach Number Inlets[J]. Journal of Propulsion Technology, 2019, 40(3): 487-495.

参考文献

[1] 李博, 袁化成, 梁德旺. 高超声速进气道等直隔离段的反压特性研究[J]. 宇航学报, 2008, 29(1): 78-83.
[2] 张堃元, 王成鹏, 杨建军, 等. 带高超进气道的隔离段流动特性[J], 推进技术, 2002, 23(4): 311-314. (ZHANG Kun-yuan, WANG Cheng-peng, YANG Jian-jun, et al. Investigation of Flow in Isolator of Hypersonic Inlet[J]. Journal of Propulsion Technology, 2002, 23(4): 311-314.)
[3] 李建平, 宋文艳. 超燃冲压发动机隔离段流动特性研究[J]. 世界科技研究与发展, 2006, 28(2): 75-78.
[4] Carroll B F, Dutton J C. Characteristics of Multiple Shock Wave/Turbulent Boundary Layer Interactions in Rectangular Ducts[J]. Journal of Propulsion and Power, 1990, 6(2): 186-193.
[5] Carroll B F, Dutton J C. Turbulence Phenomena in a Multiple Normal Shock Wave/Turbulent Boundary-Layer Interaction[J]. AIAA Journal, 1992, 30(1): 43-48.
[6] Carroll B F, Dutton J C. Multiple Normal Shock Wave/Turbulent Boundary-Layer Interactions[J]. Journal of Propulsion and Power, 1992, 8(2): 441-448.
[7] Saied Emami, Carl A Trexler, Aaron H Auslender. Experimental Investigation of Inlet-Combustor Isolators for a Dual-Mode Scramjet at a Mach Number of 4[R]. NASA TP-3502, 1995.
[8] 周航, 金志光, 曹海峰, 等. 复杂入口条件下超燃冲压发动机隔离段流动特性研究[C]. 大连:中国航天第三专业信息网第三十八届技术交流会暨第二届空天动力联合会议, 2017.
[9] Huang He-xia, Sun Shu, Tan Hui-jun, et al. Characterization of Two Typical Unthrottled Flows in Hypersonic Inlet/Isolator Models[J]. Journal of Aircraft, 2015, 52(5): 1715 –1721.
[10] He Yu-bao, Chang Jun-tao, Bao Wen, et al. Numerical Investigation of Local Resistance to Backpressure in Hypersonic Inlet with Suction[J]. Journal of Propulsion and Power, 2016, 32(6): 1531-1543.
[11] 曹学斌, 张堃元, 高亮杰. 一种带抽吸狭缝的新型短隔离段数值研究[J]. 推进技术, 2011, 32(2): 159-164. (CAO Xue-bin, ZHANG Kun-yuan, GAO Liang-jie. Numerical Investigation of a New Short Isolator with Bleed Slots[J]. Journal of Propulsion Technology, 2011, 32(2): 159-164.)
[12] Chung-Jen Tam, Dean Eklund, Robert Behdadnia, et al. Investigation of Boundary Layer Bleed for Improving Scramjet Isolator Performance[R]. AIAA 2005-3286.
[13] H?berle J, Gülhan A. Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7[J]. Journal of Propulsion and Power, 2008, 24(5): 1023-1034.
[14] Matthews A J, Jones T V, Cain T M. Design and Test of a Low-Drag Hypersonic Intake[C]. Norfolk: 12th AIAA International Space Planes and Hypersonic Systems and Technologies, 2003.
[15] 黄舶, 李祝飞, 贾立超, 等. 二维高超声速进气道内激波-边界层相互作用[J]. 中国科学技术大学学报, 2011, 41(24): 1084-1089.
[16] Herrmann C D, Koschel W W. Experimental Investigation of the Internal Compression of a Hypersonic Intake[R]. AIAA 2002-4130.
[17] Fischer C, Olivier H. Experimental Investigation of the Shock Train in an Isolator of a Scramjet Inlet[R]. AIAA 2011-2192.
[18] Xie W Z, Wu Z M, Yu A Y, et al. Control of Severe Shock-Wave/Boundary-Layer Interactions in Hypersonic Inlets[J]. Journal of Propulsion and Power, 2017, 33(10).
[19] Piegl L, Tiller W. The NURBS Book[M]. Berlin:Springer-Verlag Berlin Heidelberg, 1997.
[20] H?berle J, Gülhan A. Investigation of Two-Dimensional Scramjet Inlet Flowfield at Mach 7[J]. Journal of Propulsion and Power, 2008, 24(3): 446-459.
[21] Hohn O, Gülhan A. Experimental Investigation on the Influence of Yaw Angle on the Inlet Performance at Mach 7[R]. AIAA 2010-938.
[22] Tan H J, Sun S, Huang H X. Behavior of Shock Trains in a Hypersonic Inlet/Isolator Model with Complex BackGround Waves[J]. Experiments in Fluids, 2012, 53(6): 1647-1661.
[23] Teiichi Tamaki, Yukio Tomita, Ryuichiro Yamane. A Study of Pesudo-Shock[J]. Bulletin of the JSME, 1971, 14(74): 807-817.
[24] 王成鹏. 非对称来流条件下超燃冲压发动机隔离段气动特性研究[D]. 南京:南京航空航天大学, 2005.　　　　　　　　　　　　　　收稿日期:2017-11-29；修订日期:2017-12-28。作者简介:吴中明,硕士生,研究领域为内流气体动力学。E-mail: wzm0603@163.com通讯作者:谢文忠,博士,副教授,研究领域为内流气体动力学。E-mail: xie_wenzhong@126.com(编辑:田佳莹)