Control of Cowl Shock/Boundary Layer Interaction by Bump/Secondary Flow Circulation

Journal of Propulsion Technology ›› 2018, Vol. 39 ›› Issue (8): 1744-1752.

• Aero-thermodynamics • Previous Articles Next Articles

Control of Cowl Shock/Boundary Layer Interaction by Bump/Secondary Flow Circulation

Zhengde Polytechnic，Nanjing 211111，China and College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

唇罩激波/边界层干扰的壁面鼓包/次流循环组合控制方法研究

程代姝¹,张悦²

正德职业技术学院，江苏南京 211111,南京航空航天大学能源与动力学院，江苏南京 210016

作者简介:程代姝，女，硕士，讲师，研究领域为内流空气动力学。E-mail: fzdsO₂6@126.com 通讯作者:张悦，男，博士，讲师，研究领域为内流空气动力学。

Abstract

Abstract: To control the continuous cowl shock/boundary layer interaction in a supersonic/hypersonic inlet， a new control method by the combination of a bump and secondary flow circulation is brought forward. The flow mechanism and effects of parameters are investigated by computational method. Results show that the first cowl shock/boundary layer interaction can be controlled by the precompression effect induced by the weak compression waves at the windward side of the small-scale bump. At the same time， the low-momentum flow in the separation bubble induced by the second cowl shock is driven into the secondary flow circulation device by the pressure differential and then injected into the primary flow through the blow slot in the inlet ramp， which controls the second cowl shock/boundary layer interaction. Under the combined effect of the bump and secondary flow circulation， the separation induced by the two cowl shocks is effectively isolated and separately controlled. Meanwhile， this control method can avoid the loss of the inlet captured mass flow rate. As compared with the uncontrolled case， the bump/secondary circulation control method can realize the control of the continuous cowl shocks/boundary layer at the freestream Mach number range of 3.95～6.95. The flow in the inlet can be enhanced and the total pressure recovery ratio is improved. The most improvement of the total pressure recovery ratio can reach 15.7%. In addition， the locations of the blow slot and the bleed slot should be set appropriately to ensure the control effect.

Key words: Hypersonic/supersonic inlet；Cowl shock/boundary layer interaction；Boundary layer separation；Bump/secondary flow circulation

摘要： 为了对超声速、高超声速进气道内多道连续唇罩激波/边界层干扰现象进行有效控制，提出了一种壁面鼓包/次流循环的组合控制方法，并对相关流动机理及参数影响规律进行了研究。结果表明:通过小尺度鼓包迎风侧弱压缩波束的预增压效应，实现对第一道唇罩激波/边界层干扰的控制；同时，在压差力的驱动下，鼓包下游第二道唇罩激波作用导致的边界层分离包内的低能流进入次流循环装置，并从上游压缩面上的吹气缝喷出，实现对第二道唇罩入射激波的控制。在鼓包与次流循环装置的共同作用下，两道唇罩激波产生的边界层分离被有效隔离并分别控制。同时，本控制方案不会造成进气道捕获流量的损失。相较于无控制方案，鼓包/次流循环组合控制方案可以在来流马赫数为3.95～6.95内实现对多道连续唇罩激波/边界层干扰的控制，改善内通道中的流动，提高进气道的总压恢复性能，最大改善幅度可以达到15.7%。此外,为保证控制效果，应选择合适的吹气缝和引气缝位置。

关键词: 超声速/高超声速进气道；唇罩激波/边界层干扰；边界层分离；壁面鼓包/次流循环

CHENG Dai-shu¹,ZHANG Yue². Control of Cowl Shock/Boundary Layer Interaction by Bump/Secondary Flow Circulation[J]. Journal of Propulsion Technology, 2018, 39(8): 1744-1752.

程代姝,张悦. 唇罩激波/边界层干扰的壁面鼓包/次流循环组合控制方法研究[J]. 推进技术, 2018, 39(8): 1744-1752.

References

[1] Van Wie, D M. Scramjet Inlets[M]. Reston: American Institute of Aeronautics and Astronautics, 2000.
[2] 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.
[3] Krishnan L, Sandham N D, Steelant J. Shock-Wave/Boundary-Layer Interactions in a Model Scramjet Intake [J]. AIAA Journal, 2009, 47(7): 1680-1691.
[4] 潘宏禄, 李俊红, 沈清. 超燃进气道激波/湍流边界层干扰[J]. 推进技术, 2013, 34(9): 1172-1178. (PAN Hong-lu, LI Jun-hong , SHEN Qing. Studies of Turbulence/Shock Interaction in a Scramjet Inlet[J]. Journal of Propulsion Technology, 2013, 34(9): 1172-1178.)
[5] 谭慧俊, 李程鸿, 张悦, 等. 固定壁面激波控制技术的研究进展[J]. 推进技术, 2016, 37(11): 2001-2008. (TAN Hui-jun, LI Cheng-hong, ZHANG Yue, et al. Review of Progress in Shock Control Technology with Fixed Geometry[J]. Journal of Propulsion Technology, 2016, 37(11): 2001-2008.)
[6] 袁化成, 梁德旺. 抽吸对高超声速进气道起动能力的影响[J]. 推进技术, 2006, 27(6): 525-528. (YUAN Hua-cheng, LIANG De-wang. Effect of Suction on Starting of Hypersonic Inlet[J]. Journal of Propulsion Technology, 2006, 27(6): 525-528.)
[7] Schulte D, Henckels A, Neubacher R. Manipulation of Shock/Boundary-Layer Interactions in Hypersonic Inlets [J]. Journal of Propulsion and Power, 2001, 17(3): 585-590.
[8] H?berle J, Gülhan A. Internal Flowfield Investigation of a Hypersonic Inlet at Mach 6 with Bleed [J]. Journal of Propulsion and Power, 2007, 23(5): 1007-1017.
[9] Herrmann D, Blem S, Gulhan A. Experimental Study of Boundary-Layer Bleed Impact on Ramjet Inlet Performance [J]. Journal of Propulsion and Power, 2011, 27(6): 1186-1195.
[10] John S. Improvements in Modeling 90-Degree Bleed Holes for Supersonic Inlets[J]. Journal of Propulsion and Power, 2012, 28(4): 773-781.
[11] Knight D, Yan H, Panaras A G, et al. Advances in CFD Prediction of Shock Wave Turbulent Boundary Layer Interactions[J]. Progress in Aerospace Sciences, 2003, 39(2): 121-184.
[12] 丁晨, 刘猛, 张继华, 等. 变马赫数条件下进气道边界层吹除法数值模拟[J]. 推进技术, 2013, 34(10): 1310-1315. (DING Chen, LIU Meng, ZHANG Ji-hua, et al. Numerical Simulation on Blowing Method for Controlling Boundary Layer Interaction in Supersonic Inlet at Different Mach Number[J]. Journal of Propulsion Technology, 2013, 34(10): 1310-1315.)
[13] Shneider M N, Macheret S O, Miles R B. Analysis of Magnetohydrodynamic Control of Scramjet Inlets[J]. AIAA Journal, 2004, 42(11): 2303-2310.
[14] Bobashev S V, Erofeev A V, Lapushkina T A, et al. Effect on Magnetohydrodynamics Interaction in Various Parts of Diffuser on Inlet Shocks: Experiment[J]. Journal of Propulsion and Power, 2005, 21(5): 831-837.
[15] 苏纬仪, 陈立红, 张新宇. MHD控制激波诱导湍流边界层分离的机理分析[J]. 推进技术, 2010, 31(1): 18-23. (SU Wei-yi, CHEN Li-hong, ZHANG Xin-yu. Investigation of Magnetohydrodynamic Control on Turbulent Boundary Layer Separation Induced by Shock Wave [J]. Journal of Propulsion Technology, 2010, 31(1): 18-23.)
[16] Lee S, Goettke M K, Loth E, et al. Microramps Upstream of an Oblique-Shock/Boundary-Layer Interaction [J]. AIAA Journal, 2010, 48(1): 104-118.
[17] Ghosh S, Choi J I, Edwards J R. Numerical Simulations of Effects of Micro Vortex Generators Using Immersed-Boundary Methods[J]. AIAA Journal, 2010, 48(1): 92-103.
[18] Zhang Yue, Tan Hui-jun, Du Mo-chen, et al. Control of Shock/Boundary Layer Interaction for Hypersonic Inlets by Highly Swept Microramps[J]. Journal of Propulsion and Power, 2015, 31(1): 113-143.
[19] 苏纬仪, 陈立红, 张新宇. MHD控制激波诱导边界层分离的机理[J]. 推进技术, 2009, 30(2): 229-233. (SU Wei-yi, CHEN Li-hong, ZHANG Xin-yu. Investigation of Magnetohydrodynamic Control on Boundary Layer Separation Induced by Shock Wave[J]. Journal of Propulsion Technology, 2009, 30(2): 229-233.)
[20] 苏纬仪, 张堃元, 金志光. 高超声速进气道附面层分离无源被动控制[J]. 推进技术, 2011, 32(4): 455-460. (SU Wei-yi, ZHANG Kun-yuan, JIN Zhi-guang. Adaptive Passive Control on Hypersonic Inlet Boundary Layer Separation[J]. Journal of Propulsion Technology, 2011, 32(4): 455-460.)
[21] 张悦, 谭慧俊, 张启帆, 等. 一种进气道内激波/边界层干扰控制的新方法及其流动机理[J]. 宇航学报, 2012, 33(2): 265-274.
[22] Zhang Yue, Tan Hui-jun, Tian Fang-chao, et al. Control of Incident Shock/Boundary Layer Interaction by a Two-Dimensional Bump[J]. AIAA Journal, 2014, 52(4): 767-776.
[23] Zhang Yue, Tan Hui-jun, Sun Shu, et al. Control of Cowl Shock/Boundary Layer Interaction in Hypersonic Inlets by a Bump[J]. AIAA Journal, 2015, 53(11): 3492-3495.
[24] Tan Hui-jun, Sun Shu, Huang He-xia. Behavior of Shock Trains in a Hypersonic Inlet/Isolator Model with Complex Background Waves[J]. Experiments in Fluids, 2012, 53(6): 1647-1661.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2017-07-24；修订日期:2017-09-05。作者简介:程代姝,女,硕士,讲师,研究领域为内流空气动力学。E-mail: fzdsO₂6@126.com通讯作者:张悦,男,博士,讲师,研究领域为内流空气动力学。E-mail: y.zhang@nuaa.edu.cn

Control of Cowl Shock/Boundary Layer Interaction by Bump/Secondary Flow Circulation

唇罩激波/边界层干扰的壁面鼓包/次流循环组合控制方法研究

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments