RESEARCH PROGRESS ON HIGH-MACH-NUMBER SCRAMJET ENGINE TECHNOLOGIES
-
摘要: 吸气式高超声速飞行在空间运输和国家空天安全领域具有极高价值, 超燃冲压发动机是其核心动力装置. 目前飞行马赫数4.0 ~ 7.0超燃冲压发动机技术日趋成熟, 发展更高速的飞行动力技术成为今后临近空间竞争焦点之一. 本文对飞行马赫数8.0 ~ 10.0 的高马赫数超燃冲压发动机技术进行了分析和综述. 首先论述其亟待解决的关键问题和技术, 分别包括高焓离解与热化学非平衡效应、超高速气流燃料增混与燃烧强化技术、高超声速燃烧与进气压缩的匹配及工作模态、高焓低雷诺数边界层流动及其控制方法、高焓低密度流动/燃烧的热防护技术, 以及高马赫数发动机的地面试验风洞技术. 然后, 进一步介绍了国内外高焓激波风洞与驱动技术以及国内外典型的地面和飞行试验进展. 进而针对推进和热防护的总体性能评估、高马赫数发动机内凸显的高焓离解与热化学非平衡效应、超高速气流燃料增混和燃烧强化技术综述了相关研究进展及结论, 讨论了高马赫数超燃冲压发动机的可行性以及各关键技术的特点. 最后进行了总结并对后续研究提出了几点建议.Abstract: Hypersonic airbreathing flights are highly valued in both the fields of space transportation and national aerospace safety, and the scramjet engines are pivotal propulsion devices for these flights. The scramjet engines for flight Mach numbers within the range between 4.0 and 7.0 have been extensively studied and well developed in recent years, and the extension to the scramjet engines for higher flight Mach numbers within the range between 8.0 and 10.0 or even higher are sure to be a competing focus for near-space competitions in the following decades. The current paper analyzes and summarizes the recent research advances of scramjet engines with flight Mach numbers within the range between 8.0 and 10.0+ . First of all, the key scientific problems and technologies of the higher Mach number scramjet engines are highlighted, including the high-temperature dissociation and thermochemical nonequilibrium effects, mixing and combustion enhancement technologies in ultra-high-speed flows, the matching of hypersonic combustion and inflow compression and the operating modes, the high-enthalpy low Reynolds number boundary-layer flows and the boundary-layer flow control methods, the thermal protection technologies of high-enthalpy low-density combustion inflows, and the ground test facility technologies for high-Mach number scramjet engines, respectively. Second, the experimental apparatus related to high-enthalpy shock tunnels and the shock tunnel driving technologies and typical ground and flight experiments of the high-Mach number scramjet engines home and aboard in recent years are introduced. Third, research advances including overall performance analyses of thrusts and thermal protections, the prominent high-enthalpy dissociation and thermochemical nonequilibrium effects in high-Mach-number scramjet engines, and mixing and combustion enhancement technologies in the ultra-high-speed flows are reviewed, so as to assess the feasibilities of high-Mach-number scramjet engines, and to discuss the features of engines’ key technologies. Finally, the summary is presented and several suggestions are proposed for further studies of the higher Mach number scramjet engines.
-
表 1 不同飞行马赫数
$M{a_{\text{f}}}$ 和高度${H_{\text{f}}}$ 条件下气流的总温$T_0^*$ 和总压$p_0^*$ Table 1. Freestream
$T_0^*$ and$p_0^*$ under different flight$M{a_{\text{f}}}$ and${H_{\text{f}}}$ $M{a_{\text{f}}}$ ${H_{\text{f}}}$/km $T_0^*$/K $p_0^*$/MPa 8 30 2619 18.7 35 2710 9.2 40 2831 4.8 10 30 3688 114.7 35 3790 57.8 40 3917 31.0 12 30 4915 575.0 35 5025 296.2 40 5168 163.6 表 2 超/高超声速风洞的主要类型和特性
Table 2. Typical types and characteristics of supersonic/hypersonic test facilities
Wind tunnel type Operating time Test medium $T_0^*$/K $M{a_{\text{f}}}$ Typical wind tunnel[26] continuous minutes pure air <1000 <4 AEDC tunnels intermittent heat reservoir seconds pure air <2100 <7 HTF glenn combustion heater minutes vitiated air <2500 <8 8-ft HTT langley impulse milliseconds pure air <10000 <20 LENS 表 3 典型高焓激波风洞
Table 3. Typical high-enthalpy shock tunnels
Tunnel name Affiliation Driver type Total length/m Operating time/ms Stagnation pressure/MPa Ma T4[35] University of Queensland free piston 36 1 ~ 2 <30 4 ~ 10 FD21[36] Chinese Academy of Aerospace Aerodynamics free piston 109 2 <11 >8 LENS I[28] Calspan heated lightweight gas 26 5 ~ 15 <80 6 ~ 15 Hypulse[28] GASL lightweight gas and detonation 27 0.5 ~ 7 <30 5 ~ 12 JF24[37] Institute of Mechanics gaseous detonation 23 5 ~ 10 <20 8 ~ 12 -
[1] Urzay J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight. Annual Review of Fluid Mechanics, 2018, 50: 593-627 doi: 10.1146/annurev-fluid-122316-045217 [2] 李旭彦, 郑星, 薛瑞. 超燃冲压发动机技术发展现状及相关建议. 科技中国, 2019, 2: 5-8 doi: 10.3969/j.issn.1673-5129.2019.02.003 [3] 徐旭, 陈兵, 徐大军. 冲压发动机原理及技术. 北京: 北京航空航天大学出版社, 2014Xu Xu, Chen Bing, Xu Dajun. Ramjet Principle and Technology. Beijing: Beihang University Press, 2014 (in Chinese) [4] Builder CH. On the thermodynamic spectrum of airbreathing propulsion//1st AIAA Annual Meeting, 1964 [5] 王新月. 气体动力学基础. 西安: 西北工业大学出版社, 2006Wang Xinyue. Fundamentals of Gas Dynamics. Xi’an: Northwestern Polytechnical University Press, 2006 (in Chinese) [6] 安德森. 高超声速和高温气体动力学. 北京: 航空工业出版社, 2013(Anderson. Hypersonic and High Temperature Gas Dynamics. Beijing: Aviation Industry Press, 2013 (in Chinese) [7] 张晓源, 覃粒子, 刘宇等. 离解组分复合对超燃尾喷管性能的影响. 推进技术, 2013, 34(5): 589-594 (Zhang Xiaoyuan, Qin Lizi, Liu Yu, He Miaosheng. Effects of radical recombination on scramjet nozzle performance. Journal of Propulsion Technology, 2013, 34(5): 589-594 (in Chinese) [8] Park C, Griffith W. Nonequilibrium hypersonic aerothermodynamics. Physics Today, 1991, 44(2): 98-98 [9] Vincenti WG, Kruger CH. Introduction to physical gas dynamics. Physics Today, 1966, 19(10): 95-95 [10] Gehre RM, Wheatley V, Boyce RR. Computational investigation of thermal nonequilibrium effects in scramjet geometries. Journal of Propulsion and Power, 2013, 29(3): 648-660 doi: 10.2514/1.B34722 [11] Koo H, Raman V, Varghese PL. Direct numerical simulation of supersonic combustion with thermal nonequilibrium. Proceedings of the Combustion Institute, 2015, 35(2): 2145-2153 doi: 10.1016/j.proci.2014.08.005 [12] Fiévet R, Voelkel S, Koo H, et al. Effect of thermal nonequilibrium on ignition in scramjet combustors. Proceedings of the Combustion Institute, 2017, 36(2): 2901-2910 [13] Fiévet R, Raman V. Effect of vibrational nonequilibrium on isolator shock structure. Journal of Propulsion and Power, 2018, 34(5): 1334-1343 doi: 10.2514/1.B37108 [14] Landsberg WO, Wheatley V, Smart MK, et al. Performance of high mach number scramjets-tunnel vs. flight. Acta Astronautica, 2018, 146: 103-110 doi: 10.1016/j.actaastro.2018.02.031 [15] Wang B, Wei W, Ma SN, et al. Construction of one-step H2/O2 reaction mechanism for predicting ignition and its application in simulation of supersonic combustion. International Journal of Hydrogen Energy, 2016, 41: 19191-19206 doi: 10.1016/j.ijhydene.2016.09.010 [16] Zhang Y, Zhu SH, Chen B, et al. Hysteresis of mode transition in a dual-struts based scramjet. Acta Astronautica, 2016, 128: 147-159 doi: 10.1016/j.actaastro.2016.07.025 [17] Zhao GY, Sun MB, Wu JS, et al. Investigation of flame flashback phenomenon in a supersonic crossflow with ethylene injection upstream of cavity flameholder. Aerospace Science and Technology, 2019, 87: 190-206 doi: 10.1016/j.ast.2019.02.018 [18] Gruber MR, Nejad AS, Chen TH, et al. Mixing and penetration studies of sonic jets in a Mach 2 freestream. Journal of Propulsion and Power, 1995, 11(2): 315-323 doi: 10.2514/3.51427 [19] 沈维道, 童钧耕. 工程热力学. 北京: 高等教育出版社, 2016Shen Weidao, Tong Jungeng. Engineering Thermodynamics. Beijing: Higher Education Press, 2016 (in Chinese) [20] Lau KY. Hypersonic boundary-layer transition: application to high-speed vehicle design. Journal of Spacecraft and Rockets, 2008, 45(2): 176-183 doi: 10.2514/1.31134 [21] Chen H, Wang ZR, Zhang QF, et al. On the Reynolds-number sensitivity of inlet flow at Mach numbers beyond 7. AIAA Journal, published online [22] Heiser WH, Pratt DT. Hypersonic Airbreathing Propulsion. AIAA Education Series, AIAA, 1994 [23] 李进平. 爆轰驱动高焓激波风洞关键问题研究. [博士论文]. 北京: 中国科学院力学研究所, 2007Li Jinping. Investigation into essential problems of detonation-driven high enthalpy shock tunnels. [PhD Thesis]. Beijing: Institute of Mechanics, Chinese Academy of Sciences, 2007 (in Chinese) [24] 唐志共, 许晓斌, 杨彦广等. 高超声速风洞气动力试验技术进展. 航空学报, 2015, 36(1): 86-97 (Tang Zhigong, Xu Xiaobin, Yang Yanguang, et al. Research progress on hypersonic wind tunnel aerodynamic testing techniques. Acta Aeronautica Et Astronautica Sinica, 2015, 36(1): 86-97 (in Chinese) [25] 贺元元, 吴颖川, 张小庆等. 脉冲燃烧风洞与常规高超声速风洞数据相关性研究. 实验流体力学, 2018, 32(3): 64-68 (He Yuanyuan, Wu Yingchuan, Zhang Xiaoqing, et al. Analysis of data correlation between combustion heated impulse facility and hypersonic wind tunnel. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 64-68 (in Chinese) doi: 10.11729/syltlx20180011 [26] Lu F, Marren D. Advanced hypersonic test facilities//Progress in Astronautics and Aeronautics, 2002: 198 [27] Fotia ML, Driscoll JF. Isolator-combustor interactions in a direct-connect ramjet-scramjet experiment. Journal of Propulsion and Power, 2012, 28(1): 83-95 doi: 10.2514/1.B34367 [28] Gu S, Olivier H. Capabilities and limitations of existing hypersonic facilities. Progress in Aerospace Sciences, 2020, 113: 100607 doi: 10.1016/j.paerosci.2020.100607 [29] Wang YP, Hu ZM, Liu YF, et al. Starting process in a large-scale shock tunnel. AIAA Journal, 2016, 54(4): 1-10 [30] 姜宗林, 李进平, 胡宗民等. 高超声速飞行复现风洞理论与方法. 力学学报, 2018, 50(6): 1283-1291 (Jiang Zonglin, Li Jinping, Hu Zongmin, et al. Shock tunnel theory and methods for duplicating hypersonic flight conditions. Chinese Journal of Theoretical and Applied Mechanics, 2018, 50(6): 1283-1291 (in Chinese) doi: 10.6052/0459-1879-18-238 [31] Michael SH, Timothy PW, Matthew M, et al. Experimental research and analysis in supersonic and hypervelocity flows in the lens shock tunnels and expansion tunnel//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 [32] Klaus H, Katsuhiro I, David JM, et al. Free Piston Shock Tunnels HEG, HIEST, T4 and T5. Springer International Publishing, 2016 [33] Jiang ZL, Hu ZM, Wang YP, et al. Advances in critical technologies for hypersonic and high-enthalpy wind tunnel. Chinese Journal of Aeronautics, 2020, 33(12): 12 [34] 姜宗林, 俞鸿儒. 高焓激波风洞研究进展//中国力学学会学术大会, 郑州市, 2009 [35] Stalker RJ, Paull A, Mee DJ, et al. Scramjets and shock tunnels - the queensland experience. Progress in Aerospace Sciences, 2005, 41(6): 471-513 doi: 10.1016/j.paerosci.2005.08.002 [36] 卢洪波, 张冰冰, 沈清等. 新建高焓激波风洞 Ma=8 飞行模拟条件的实现与超燃实验. 气体物理, 2019, 4(5): 13-24 (Lu Hongbo, Zhang Bingbing, Shen Qing, et al. Flight condition achievement of Mach number 8 in a new shock tunnel of CAAA and its scramjet experimental investigation. Physics of Gases, 2019, 4(5): 13-24 (in Chinese) [37] 张旭, 张启帆, 岳连捷等. 高马赫数燃烧强化的激波风洞试验研究. 力学学报, 2021, 53(11): 1-11 (Zhang Xu, Zhang Qifan, Yue Lianjie, et al. Shock-tunnel experimental study of combustion enhancement methods for a high-Mach-number scramjet. Chinese Journal of Theoretical and Applied Mechanics, 2021, 53(11): 1-11 (in Chinese) doi: 10.6052/0459-1879-xx-xxx [38] 陆星宇, 李进平, 陈宏等. 爆轰驱动高能起爆技术实验研究. 中国科学, 2019, 49(3): 311-319 (Lu Xingyu, Li Jinping, Chen Hong, et al. Experimental research on high energy initiation technology for detonation driver. Scientia Sinica Technologica, 2019, 49(3): 311-319 (in Chinese) doi: 10.1360/N092018-00029 [39] Marshall LA, Bahm C, Corpening GP, et al. Overview with results and lessons learned of the X-43 A Mach 10 flight//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, 2005 [40] Rogers RC, Shih AT, Hass NE. Scramjet development tests supporting the Mach 10 flight of the X-43//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, 2005 [41] 范培蕾, 杨涛, 张晓今等. 高超声速低成本飞行试验进展. 导弹与航天运载技术, 2008, 6: 17-22 (Fan Peilei, Yang Tao, Zhang Xiaojin, et al. Progress on hypersonic vehicle's low-cost flight experiment. Missiles and Space Vehicles, 2008, 6: 17-22 (in Chinese) doi: 10.3969/j.issn.1004-7182.2008.06.005 [42] Pauli A, Alesi H, Anderson S. The Development of the HyShot Flight Program. Shock Waves. Berlin, Heidelberg: Springer, 2005 [43] Smart MK, Hass NE, Paull A. Flight data analysis of the HyShot 2 scramjet flight experiment. AIAA Journal, 2006, 44(10): 2366-2375 doi: 10.2514/1.20661 [44] Ground testing of the HyShot supersonic combustion flight experiment in HEG and comparison with flight data//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004 [45] 邓帆, 尘军, 谢峰等. 基于超燃冲压发动机的HIFiRE项目飞行试验研究进展. 航空动力学报, 2018, 33(3): 683-695 (Deng Fan, Chen Jun, Xie Feng, et al. Research progress on flight tests of HIFiRE project based on scramjet. Journal of Aerospace Power, 2018, 33(3): 683-695 (in Chinese) [46] Kevin B, Alan P, Douglas D, et al. HiFire: an international collaboration to advance the science and technology of hypersonic flight//28th International Congress of the Aeronautical Sciences, 2012 [47] Kevin RJ, Mark RG, Salvatore B. Mach 6–8+ hydrocarbon-fueled scramjet flight experiment: the HIFiRE flight 2 project. Journal of Propulsion and Power, 2015, 31(1): 36-53 doi: 10.2514/1.B35350 [48] Russell B, Tim M, Sean O, et al. Combustion scaling laws and inlet starting for Mach 8 inlet-injection radical farming scramjets//Air Force Research Lab Wright-Patterson AFB, OH, 2010 [49] Sarah AR, Todd BS, Michael KS, et al. The HIFiRE 7 flight experiment//22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, 2018 [50] Smart MK, Suraweera MV. HIFire 7-development of a 3D scramjet for flight testing//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 2009 [51] Walker SH, Rodgers F. Falcon hypersonic technology overview//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies, 2005 [52] Walker SH, Sherk J , Shell D, et al. The DARPA/AF Falcon Program: The hypersonic technology vehicle #2 (HTV-2) flight demonstration phase//AIAA International Space Planes & Hypersonic Systems & Technologies Conference, 2008 [53] Walker S, Rodgers F, Paull A, et al. HyCAUSE flight test program//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008 [54] Walker SH, Rodgers FC, Esposita AL. Hypersonic collaborative Australia/United States experiment (HYCAUSE)//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies, 2005 [55] Boyce RR, Tirtey SC, Brown L, et al. SCRAMSPACE : scramjet-based access-to-space systems//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2011 [56] Tirtey SC, Boyce RR, Brown LM, et al. The SCRAMSPACE I scramjet flight design and construction//18th AIAA/3 AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012 [57] Brown LM, Tirtey SC, van Staden PA, et al. Static stability of the SCRAMSPACE I Mach 8 hypersonic flight experiment//18th AIAA/3 AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012 [58] Boyce RR, Schramm JM, Oberg D, et al. Shock tunnel and numerical studies of a large inlet-fuelled inward turning axisymmetric scramjet//18th AIAA/3 AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012 [59] Kurtz J, Aizengendler M, Krishna Y, et al. Flight test of a rugged scramjet-inlet temperature and velocity sensor//53rd AIAA Aerospace Sciences Meeting, 2015 [60] Sunami T, Murakami A, Kudo K, et al. Mixing and combustion control strategies for efficient scramjet operation in wide range of flight mach number//11th AIAA/AAAF International Conference Space Planes and Hypersonic Systems and Technologies, 2002 [61] Sunami T, Scheel F. Analysis of mixing enhancement using streamwise vortices in a supersonic combustor by application of laser diagnostics//11th AIAA/AAAF International Conference Space Planes and Hypersonic Systems and Technologies, 2002 [62] Sunami T, Magre P, Bresson A, et al. Experimental study of strut injectors in a supersonic combustor using OH-PLIF//13th International Space Planes and Hypersonic Systems and Technologies Conference, 2005 [63] . Sunami T, Itoh K, Satoh K, et al. Mach 8 ground tests of the hypermixer scramjet for HyShot-IV flight experiment//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, 2006 [64] 姚轩宇, 王春, 喻江等. JF12激波风洞高Mach数超燃冲压发动机实验研究. 气体物理, 2019, 4(5): 26-31 (Yao Xuanyu, Wang Chun, Yu Jiang, et al. High-mach-number scramjet engine tests in JF12 shock tunnel. Physics of Gases, 2019, 4(5): 26-31 (in Chinese) [65] 吴里银, 孔小平, 李贤等. 马赫数10超燃冲压发动机激波风洞实验研究. 推进技术, 2021, 42(12): 12Wu Liyin, Kong Xiaoping, Li Xian, et al. Experimental study on a scramjet at Mach 10 in shock tunnel. Journal of Propulsion Technology, 2021, 42(12): 12 (in Chinese) [66] Zhou GX, Zhang X, Li JP, et al. Optical diagnostics in a detonation-driven direct-connected circular combustor fueled with hydrogen for Mach 10 scramjet. Journal of Hydrogen Energy, 2021, 46(54): 27801-27815 doi: 10.1016/j.ijhydene.2021.06.004 [67] Waltrup PJ. Upper bounds on the flight speed of hydrocarbon-fueled scramjet-powered vehicles. Journal of Propulsion and Power, 2001, 17(6): 1199-1204 doi: 10.2514/2.5895 [68] Wang YY, Cheng KL, Tang JF, et al. Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement. Aerospace Science and Technology, 2019, 98: 105594 [69] Smart MK. How much compression should a scramjet inlet do. AIAA Journal, 2012, 50(3): 610-619 doi: 10.2514/1.J051281 [70] Zhang D, Yang SB, Zhang SL, et al. Thermodynamic analysis on optimum performance of scramjet engine at high Mach numbers. Energy, 2015, 90: 1046-1054 doi: 10.1016/j.energy.2015.08.017 [71] Cao RF, Chang JT, Tang JF, et al. Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis. International Journal of Hydrogen Energy, 2014, 39(36): 21251-21258 doi: 10.1016/j.ijhydene.2014.10.082 [72] Roux JA, Shakya N, Choi J. Revised parametric ideal scramjet cycle analysis. Journal of Thermophysics and Heat Transfer, 2013, 27(1): 178-183 doi: 10.2514/1.T3961 [73] Ji ZF, Zhang HQ, Wang B. Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine. Journal of Aerospace Engineering, 2019, 233(13): 4810-4824 [74] Yang QC, Zong YH, Wen B. Constant static-temperature heating for hydrogen fueled scramjet engine. International Journal of Hydrogen Energy, 2016, 41(3): 2002-2010 doi: 10.1016/j.ijhydene.2015.11.014 [75] 徐雪睿, 仲峰泉. 解离效应对超燃冲压发动机燃烧与传热的影响特性研究. 推进技术, 2021, 出版中Xu Xuerui, Zhong Fengquan. Effects of dissociation on combustion and heat transfer of scramjet. Journal of Propulsion Technology, 2021, in press (in Chinese) [76] Zhu YH, Peng W, Xu RN, et al. Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles. Chinese Journal of Aeronautics, 2018, 31(10): 1929-1953 doi: 10.1016/j.cja.2018.06.011 [77] 章思龙, 秦江, 周伟星等. 高超声速推进再生冷却研究综述. 推进技术, 2018, 39(10): 23-36 (Zhang Silong, Qin Jiang, Zhou Weixing, et al. Review on regenerative cooling technology of hypersonic propulsion. Journal of Propulsion Technology, 2018, 39(10): 23-36 (in Chinese) [78] 金烜, 沈赤兵, 吴先宇等. 超燃冲压发动机再生冷却技术研究进展. 火箭推进, 2016, 42(5): 66-73 (Jin Xuan, Shen Chibing, Wu Xianyu, et al. Progress of regenerative cooling technology for scramjet. Journal of Rocket Propulsion, 2016, 42(5): 66-73 (in Chinese) doi: 10.3969/j.issn.1672-9374.2016.05.012 [79] Zhang C, Qin J, Yang QC, et al. Design and heat transfer characteristics analysis of combined active and passive thermal protection system for hydrogen fueled scramjet. International Journal of Hydrogen Energy, 2015, 40(1): 675-682 doi: 10.1016/j.ijhydene.2014.11.036 [80] 罗世彬, 吴先宇, 罗文彩等. 机身/推进系统一体化高超声速飞行器冷却性能分析. 弹箭与制导学报, 2004, 24(1): 56-62 (Luo Shibin, Wu Xianyu, Luo Wencai, et al. Cooling analysis of an airframe /propulsion integrated hypersonic vehicle. Journal of Projectiles, Rockets, Missiles and Guidance, 2004, 24(1): 56-62 (in Chinese) doi: 10.3969/j.issn.1673-9728.2004.01.020 [81] Zhong FQ, Fan XJ, Yu G, et al. Thermal cracking and heat sink capacity of aviation kerosene under supercritical conditions. Journal of Thermophysics and Heat Transfer, 2011, 25(3): 1226-1232 [82] 刘朝晖, 宋晨阳, 陈强等. 吸热型碳氢燃料再生冷却性能评估方法. 火箭推进, 2020, 46(2): 15-20 (Liu Zhaohui, Song Chenyang, Chen Qiang, et al. Evaluation methods on regenerative cooling performance for endothermic hydrocarbon fuel. Journal of Rocket Propulsion, 2020, 46(2): 15-20 (in Chinese) doi: 10.3969/j.issn.1672-9374.2020.02.003 [83] Qin J, Bao W, Zhang SL, et al. Comparison during a scramjet regenerative cooling and recooling cycle. Journal of Thermophysics and Heat Transfer, 2012, 26(4): 612-618 doi: 10.2514/1.T3820 [84] 张晓嘉, 岳连捷, 张新宇. 大内收缩比二元高超声速进气道波系配置特性. 推进技术, 2012, 4(33): 505-509 (Zhang Xiaojia, Yue Lianjie, Chang Xinyu. Shocks arrangement of ramp compression hypersonic inlet with high internal contraction ratio. Journal of Propulsion Technology, 2012, 4(33): 505-509 (in Chinese) [85] 张启帆, 岳连捷, 贾轶楠等. 真实气体效应对Ma10级进气道流动的影响. 推进技术, 2019, 40(5): 1042-1050 (Zhang Qifan, Yue Lianjie, Jia Yinan, et al. Real-gas effects on hypersonic inlet flow at Mach 10. Journal of Propulsion Technology, 2019, 40(5): 1042-1050 (in Chinese) [86] Xiao YB, Yue LJ, Ma SH, et al. Design methodology for shape transition inlets based on constant contraction of discrete streamtubes. Journal of Aerospace Engineering, 2016, 230(8): 1496-1506 doi: 10.1177/0954410015613112 [87] 代春良, 孙波, 梁晓扬等. 真实气体效应下高马赫数内转进气道特性研究. 推进技术, 2020, 41(7): 1473-1483 (Dai Chunliang, Sun Bo, Liang Xiaoyang, et al. Study on characteristics of high mach number inward turning inlet under real gas effect. Journal of Propulsion Technology, 2020, 41(7): 1473-1483 (in Chinese) [88] Huang TL, Yue LJ, Ma SH, et al. Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator. Chinese Journal of Aeronautics, 2020, 33(12): 3176-3188 doi: 10.1016/j.cja.2020.04.019 [89] Lorrain P. Flow structure/chemistry coupling in the ignition process in shock-induced-combustion scramjets. [PhD Thesis]. Brisbane: School of Mechanical and Mining Engineering, University of Queensland, 2014 [90] Han S, Lee S, Lee BJ. Numerical analysis of thermochemical nonequilibrium flows in a model scramjet engine. Energies, 2020, 13: 1-17 [91] Micka DJ. Combustion stabilization, structure, and spreading in a laboratory dual-mode scramjet combustor. [PhD Thesis]. Michigan: The University of Michigan, 2010 [92] Peng JB, Cao Z, Xin Y, et al. Analysis of combustion instability of hydrogen fueled scramjet combustor on high-speed OH-PLIF measurements and dynamic mode decomposition. International Journal of Hydrogen Energy, 2020, 45(23): 13108-13118 doi: 10.1016/j.ijhydene.2020.02.216 [93] Stalker RJ, Truong NK, Morgan RG, et al. Effects of hydrogen-air non-equilibrium chemistry on the performance of a model scramjet thrust nozzle. Aeronautical Journal -New Series, 2004, 108(1089): 575-584 doi: 10.1017/S0001924000000403 [94] Huang Y, Wang PY, Dou Y, et al. Chemical non-equilibrium flow analysis of H2 fueled scramjet nozzle. Case Studies in Thermal Engineering, 2015, 5: 89-97 doi: 10.1016/j.csite.2015.02.002 [95] Zhang XY, Qin LZ, Chen H, et al. Radical recombination in a hydrocarbon-fueled scramjet nozzle. Chinese Journal of Aeronautics, 2014, 27(6): 1413-1420 doi: 10.1016/j.cja.2014.10.007 [96] Yao W, Chen L. Large eddy simulation of REST hypersonic combustor based on dynamic zone flamelet model//AIAA Propulsion and Energy 2020 Forum, 2020 [97] Yao W. On the application of dynamic zone flamelet model to large eddy simulation of supersonic hydrogen flame. International Journal of Hydrogen Energy, 2020, 45(41): 21940-21955 doi: 10.1016/j.ijhydene.2020.05.189 [98] Petty DJ, Wheatley V, Smart MK, et al. Effects of oxygen enrichment on scramjet performance. AIAA Journal, 2013, 51(1): 226-235 doi: 10.2514/1.J051732 [99] Turner JC, Smart MK. Application of inlet injection to a three-dimensional scramjet at Mach 8. AIAA Journal, 2010, 48(4): 829-838 doi: 10.2514/1.J050052 [100] Barth JE, Wheatley V, Smart MK. Effects of hydrogen fuel injection in a Mach 12 scramjet inlet. AIAA Journal, 2015, 53(10): 2907-2919 doi: 10.2514/1.J053819 [101] Capra BR, Boyce RR, Kuhn M, et al. Porous versus porthole fuel injection in a radical farming scramjet: a numerical analysis. Journal of Propulsion and Power, 2015, 31(3): 1-15 [102] Judy O. Scramjet experiments using radical farming. [PhD Thesis]. Brisbane: The University of Queensland, 2004 [103] Suraweera MV, Smart MK. Shock-tunnel experiments with a Mach 12 rectangular-to-elliptical shape-transition scramjet at offdesign conditions. Journal of Propulsion and Power, 2009, 25(3): 555-564 doi: 10.2514/1.37946 [104] Doherty LJ, Smart MK, Mee DJ. Experimental testing of an airframe-integrated three-dimensional scramjet at Mach 10. AIAA Journal, 2015, 53(11): 1-12 [105] Landsberg WO, Wheatley V, Smart MK, et al. Enhanced supersonic combustion targeting combustor length reduction in a Mach 12 scramjet. AIAA Journal, 2018, 56(10): 3802-3807 [106] Barth JE, Wise DJ, Wheatley V, et al. Tailored fuel injection for performance enhancement in a Mach 12 scramjet engine. Journal of Propulsion and Power, 2018, 35(1): 1-15 [107] Barth JE, Wheatley V, Smart MK. Hypersonic turbulent boundary-layer fuel injection and combustion: skin-friction reduction mechanisms. AIAA Journal, 2013, 51(9): 2147-2157 doi: 10.2514/1.J052041 [108] Kirchhartz RM, Mee DJ, Stalker RJ. Supersonic skin-friction drag with tangential wall slot fuel injection and combustion. AIAA Journal, 2012, 50(2): 313-324 doi: 10.2514/1.J051073 [109] Viti V, Neel R, Schetz JA. Detailed flow physics of the supersonic jet interaction flow field. Physics of Fluids, 2009, 21(4): 296 [110] Razzaqi SA, Smart MK. Hypervelocity experiments on oxygen enrichment in a hydrogen-fueled scramjet. AIAA Journal, 2011, 49(7): 1488-1497 doi: 10.2514/1.J050866 [111] Capra BR. Porous fuel injection with oxygen enrichment in a viable scramjet engine//19th Australasian Fluid Mechanics Conference, 2014 [112] Capra BR, Boyce RR, Kuhn M, et al. Combustion enhancement in a scramjet engine using oxygen enrichment and porous fuel injection. Journal of Fluid Mechanics, 2015, 767: 173-198 doi: 10.1017/jfm.2015.43 [113] 张岩, 李崇香, 韦宝禧等. 超燃冲压发动机燃料喷注方案综述. 飞航导弹, 2014, 2: 61-67 [114] 刘昊, 张蒙正, 豆飞龙. 超燃冲压发动机支板研究综述. 火箭推进, 2016, 42(5): 74-81 (Liu Hao, Zhang Mengzheng, Dou Feilong. Research on strut of scramjet engine. Journal of Rocket Propulsion, 2016, 42(5): 74-81 (in Chinese) doi: 10.3969/j.issn.1672-9374.2016.05.013 [115] 李宁, 李旭昌, 张涵等. 超声速燃烧火焰稳定技术及其发展综述. 飞航导弹, 2014, 5: 60-67 [116] Chang JT, Zhang JL, Bao W, et al. Research progress on strut-equipped supersonic combustors for scramjet application. Progress in Aerospace Sciences, 2018, 103: 1-30 doi: 10.1016/j.paerosci.2018.10.002 [117] Rust B, Gerlinger P, Aigner M. An improved lobed strut injector concept for supersonic combustion//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010 [118] Hiejima T, Oda T. Shockwave effects on supersonic combustion using hypermixer struts. Physics of Fluids, 2020, 32(1): 016104 [119] Gerlinger P, Stoll P, Kindler M. Numerical investigation of mixing and combustion enhancement in supersonic combustors by strut induced streamwise vorticity. Aerospace Science and Technology, 2008, 12: 159-168 [120] Hiejima T. Effects of streamwise vortex breakdown on supersonic combustion. Physical Review E, 2016, 93(4): 043115 -