SPECIAL SECTION: AIR-BREATHING ENGINE AND AEROSPACE POWER TECHNOLOGY |
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Skin friction reduction for boundary layer combustion in a scramjet engine |
HE Xin1, XUE Rui1, ZHENG Xing1, ZHANG Qian1, GONG Jianliang2 |
1. State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi'an Jiaotong University, Xi'an 710049, China; 2. Xi'an Modern Chemistry Research Institute, Xi'an 710065, China |
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Abstract The skin friction characteristics for boundary layer combustion in a scramjet engine were studied numerically by analyzing the effect of adding a boundary layer combustion device and for changes in the scramjet exhaust nozzle lower wall inclination angle. The combustion was modeled using a hydrogen-air kinetics model consisting of 9 species and 27 reaction steps with the flow modeled. The turbulence was modeled using the four-equation Transition SST (shear stress transport) turbulence model which takes account the boundary layer transition to accurately predict the hydrogen combustion in the boundary layer with the hydrogen injected from the boundary layer combustion device. The investigation of the effects of various exhaust nozzle lower wall inclination angles shows that the flow expansion inhibits boundary layer combustion in the combustion chamber while dramatically reducing the skin friction in the exhaust nozzle. In contrast, a contracting exhaust nozzle enhances the boundary layer combustion in the combustion chamber while increasing the flow resistance. However, the boundary layer flame is extinguished before it propagates into the nozzle section, which further increases the skin friction. Thus, if the boundary layer combustion flame can be spread into and stabilized in the nozzle section, the scramjet with a contraction profile will exhibit superior skin friction reductions.
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Keywords
scramjet engine
boundary layer combustion
skin friction resistance reduction
numerical simulation
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Issue Date: 10 March 2022
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[1] ANDERSON J D J. Hypersonic and high-temperature gas dynamics[M]. 2nd ed. Reston:American Institute of Aeronautics and Astronautics, 2006. [2] PAULL A, STALKER R, MEE D. Experiments on supersonic combustion ramjet propulsion in a shock tunnel[J]. Journal of Fluid Mechanics, 1999, 296(1):159-183. [3] 郭杰, 耿兴国, 高鹏, 等. 边界层控制法减阻技术研究进展[J]. 鱼雷技术, 2008, 16(1):1-6.GUO J, GENG X G, GAO P, et al. Recent development of dag reduction technologies via boundary layer control[J]. Torpedo Technology, 2008, 16(1):1-6. (in Chinese) [4] 杨弘炜, 高歌. 一种新型边界层控制技术应用于湍流减阻的实验研究[J]. 航空学报, 1997, 18(4):72-84.YANG H W, GAO G. Experimental study for turbulent drag reduction using a novel boundary control technique[J]. Acta Aeronautica et Astronautica Sinica, 1997, 18(4):72-74. (in Chinese) [5] 徐中, 徐宇, 王磊, 等. 凹坑形表面在空气介质中的减阻性能研究[J]. 摩擦学学报, 2009, 29(6):579-583.XU Z, XU Y, WANG L, et al. Drag reduction effect of dimple concave surface in air[J]. Tribology, 2009, 29(6):579-583. (in Chinese) [6] 孙宗祥. 等离子体减阻技术的研究进展[J]. 力学进展, 2003, 33(1):87-94.SUN Z X. Progress in plasma assisted drag reduction technology[J]. Advances in Mechanics, 2003, 33(1):87-94. (in Chinese) [7] 罗金玲, 徐敏, 戴梧叶, 等. 高速飞行器等离子体减阻的数值模拟研究[J]. 宇航学报, 2009, 30(1):119-122.LUO J L, XU M, DAI W Y, et al. Numerical simulation investigation on plasma injection for drag reduction of hypersonic vehicle[J]. Journal of Astronautics, 2009, 30(1):119-122. (in Chinese) [8] CORKE T C, THOMAS F O. Active and passive turbulent boundary-layer drag reduction[J]. AIAA Journal, 2018, 56(10):3835-3847. [9] 王宇天, 张百灵, 李益文, 等. 等离子体激励控制激波与边界层干扰流动分离数值研究[J]. 航空动力学报, 2018, 33(2):364-371.WANG Y T, ZHANG B L, LI Y W, et al. Numerical investigation for control of shock wave and boundary layer interactions flow separation with plasma actuation[J]. Journal of Aerospace Power, 2018, 33(2):364-371. (in Chinese) [10] STALKER R J. Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen[J]. Journal of Spacecraft and Rockets, 2005, 45(4):577-587. [11] CLARK R J, SHRESTHA S O B. Boundary layer combustion for skin friction drag reduction in scramjet combustors[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Cleveland, USA:AIAA, 2014. [12] ROWAN S, PAULL A. Viscous drag reduction in a scramjet combustor with film cooling[C]//10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference. Kyoto, Japan:AIAA, 2001. [13] SURAWEERA M V. Reduction of skin friction drag in hypersonic flow by boundary layer[D]. Brisbane:University of Queensland, 2006. [14] LARIN O B, LEVIN V A. Flow in a turbulent supersonic boundary layer with a heat source[J]. Technical Physics Letters, 1999, 25(4):265-266. [15] PUDSEY A S, BOYCE R R, WHEATLEY V. Hypersonic viscous drag reduction via multiporthole injector arrays[J]. Journal of Propulsion and Power, 2013, 29(5):1087-1096. [16] ZHANG P, XU J L, YU Y, et al. Effect of adverse pressure gradient on supersonic compressible boundary layer combustion[J]. Aerospace Science and Technology, 2019, 88:380-394. [17] 王帅, 何国强, 秦飞, 等. 超声速内流道摩擦阻力分析及减阻技术研究[J]. 航空动力学报, 2019, 34(4):908-919.WANG S, HE G Q, QIN F, et al. Research on skin-frictiondrag and drag reduction technics in a supersonic inner flow path[J]. Journal of Aerospace Power, 2019, 34(4):908-919. (in Chinese) [18] GAO Z X, JIANG C W, PAN S W, et al. Combustion heat-release effects on supersonic compressible turbulent boundary layers[J]. AIAA Journal, 2015, 53(7):1949-1968. [19] YU K, XU J, LIU S, et al. Starting characteristics and phenomenon of a supersonic wind tunnel coupled with inlet model[J]. Aerospace Science and Technology, 2018, 77:626-37. [20] QIN Q H, XU J L, GUO S. Fluid-thermal analysis of aerodynamic heating over spiked blunt body configurations[J]. Acta Astronautica, 2017, 132:230-242. [21] MARINOV N M, WESTBROOK C K, PITZ W J. Detailed and global chemical kinetics model for hydrogen[C]//8th International Symposium on Transport Properties. Washington, DC, USA:USDOE, 1995. [22] XUE R, ZHENG X, YUE L J, et al. Study of shock train/flame interaction and skin-friction reduction by hydrogen combustion in compressible boundary layer[J]. International Journal of Hydrogen Energy, 2020, 45(31):15683-15696. [23] XUE R, ZHENG X, YUE L J, et al. Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion[J]. Acta Astronautica, 2020, 174:11-23. [24] MCRAE C, JOHANSEN C T, DANEHY P M, et al. OH PLIF visualization of the UVA supersonic combustion experiment:Configuration A[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Grapevine, USA:AIAA, 2013. |
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