进口条件对超燃冲压发动机氢气燃烧流场特性的影响分析
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摘要
对不同进口条件下的超燃冲压发动机燃烧室内氢气喷流超声速燃烧流动特性进行了数值模拟与分析.宽范围超燃冲压发动机是吸气式高超声速飞行器推进系统设计中的热点问题之一,受实验设备硬件条件及实验技术限制,数值模拟技术仍然是超燃冲压发动机燃烧室内燃气燃烧特性及流场特性的主要研究手段.采用基于混合网格技术的多组元N-S方程有限体积方法求解器,在不同进口Mach数及压强条件下,对带楔板/凹腔结构的燃烧室模型氢气喷流燃烧流场进行了数值模拟,对比分析了氢气喷流穿透深度、喷口前后回流区结构、掺混效率及燃烧效率等流场结构与典型流场参数的变化特性及影响规律.研究成果可为宽范围超燃冲压发动机喷流燃烧流动特性分析提供参考.
The characteristics of hydrogen transverse jet supersonic combustion flow field of scramjet under different inlet conditions were numerically simulated and analyzed. Numerical simulation technology is the main method to study the fuel combustion and flow field structure of wide range scramjet, due to the limitation of experimental technology and equipment.Based on the hybrid mesh, the finite volume method for multi-component N-S equations solver was used to simulate the flow of hydrogen transverse jet combustion in the supersonic combustor with wedge/cavity structure, with different Mach numbers and pressures of inlet. The penetration depth of the hydrogen jet, the structure of separation around jet, the mixing efficiency and the combustion efficiency were discussed to show the change of flow field. The results can offer some references for the analysis of the jet combustion flow field in a wide range scramjet.
The characteristics of hydrogen transverse jet supersonic combustion flow field of scramjet under different inlet conditions were numerically simulated and analyzed. Numerical simulation technology is the main method to study the fuel combustion and flow field structure of wide range scramjet, due to the limitation of experimental technology and equipment.Based on the hybrid mesh, the finite volume method for multi-component N-S equations solver was used to simulate the flow of hydrogen transverse jet combustion in the supersonic combustor with wedge/cavity structure, with different Mach numbers and pressures of inlet. The penetration depth of the hydrogen jet, the structure of separation around jet, the mixing efficiency and the combustion efficiency were discussed to show the change of flow field. The results can offer some references for the analysis of the jet combustion flow field in a wide range scramjet.
引文
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[21]席文雄,孙明波,李庆.超声速气流中的斜激波诱导自点火[J].航空动力学报,2016,31(2):377-382.Xi W X,Sun M B,Li Q.Self-ignition in supersonic flow induced by oblique shock wave[J].Journal of Aerospace Power,2016,31(2):377-382(in Chinese).
[22]樊孝峰,王江峰,赵法明.Roe格式在多组元燃烧流场数值模拟中的应用[J].南京航空航天大学学报,2016,48(3):347-351.Fan X F,Wang J F,Zhao F M.Numerical simulation of multi-component reacting flow using Roe scheme[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(3):347-351(in Chinese).
[23]刘晨.复杂燃烧流场数值模拟方法研究[D].南京:南京航空航天大学,2009.Liu C.Numerical methods for complex combustion flowfields[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2009(in Chinese).
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[26]Menter F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[27]田野,杨顺华,肖保国,等.空气节流对煤油燃料超燃燃烧室燃烧性能影响[J].宇航学报,2015,36(12):1421-1427.Tian Y,Yang S H,Xiao B G,et al.Effect of air throttling on combustion performance of a kerosene-fueled scramjet combustor[J].Journal of Astronautics,2015,36(12):1421-1427(in Chinese).
[28]胡如云,王亮,符松.后台阶流动及其控制述评[J].中国科学:物理学力学天文学,2015,45(12):44-53.Hu R Y,Wang L,Fu S.Review of backward-facing step flow and separation reduction[J].Scientia Sinica:Physica,Mechanica&Astronomica,2015,45(12):44-53(in Chinese).
[29]Segal C.The scramjet engine:processes and characteristics[M].Hardback:Cambridge University Press,2009.
[30]Baurle R,Mathur T,Gruber M,et al.A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications[C].Proceedings of the 34th AIAA/ASME//SAE/ASEE Joint Propulsion Conference and Exhibit,Joint Propulsion Conferences,Cleveland,OH,USA:AIAA,2013.
[2]Mura A,Izard J F.Numerical simulation of supersonic nonpremixed turbulent combustion in a scramjet combustor model[J].Journal of Propulsion and Power,2010,26(4):858-868.
[3]Pudsey A S,Boyce R R.Numerical investigation of transverse jets through multiport injector arrays in a supersonic crossflow[J].Journal of Propulsion and Power,2010,26(6):1225-1236.
[4]Shekarian A A,Tabejamaat S,Shoraka Y.Effects of incident shock wave on mixing and flame holding of hydrogen in supersonic air flow[J].International Journal of Hydrogen Energy,2014,39(19):10284-10292.
[5]李朗,陈国平,张伟.超燃冲压发动机燃烧流场及火焰稳定初步研究[J].应用力学学报,2016,33(2):208-214.Li L,Chen G P,Zhang W.Preliminary study on flame stabilization and combustion field of a scramjet combustor[J].Chinese Journal of Applied Mechanics,2016,33(2):208-214(in Chinese).
[6]宋冈霖,陈华强,韦宝禧,等.基于气动斜坡的超燃冲压发动机双燃烧室方案研究[J].航空发动机,2017,43(2):41-47.Song G L,Chen H Q,Wei B X,et al.Study on dualcombustor scramjet based on aero-ramp injector[J].Aeroengine,2017,43(2):41-47(in Chinese).
[7]周驯黄,陈荣钱,李怡庆,等.椭圆形超燃燃烧室内燃料喷射和掺混性能研究[J].推进技术,2017,38(3):637-645.Zhou X H,Chen R Q,Li Y Q,et al.Injection and mixing performance in an elliptical scramjet combustor[J].Journal of Propulsion Technology,2017,38(3):637-645(in Chinese).
[8]裴崇志,谭宇,黄思源,等.超燃冲压发动机圆形与矩形燃烧室凹槽流场比较研究[C].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论文集---吸气式与组合推进技术,大连:中国航天第三专业信息网,2017:11.Pei C Z,Tan Y,Huang S Y,et al.Comparative study of flow field in a circular and rectangular combustor of scramjet[C].Process of 38thTechnical Exchange Conference and the Second Air and Space Power Conference:Inspiratory and Combined Propulsion Technology,Dalian:2017:11(in Chinese).
[9]李俊红,潘宏禄,沈清,等.超燃冲压发动机燃烧室的燃烧特性[J].航空动力学报,2014,29(1):14-22.Li J H,Pan H L,Shen Q,et al.Combustion characteristics of scramjet combustor[J].Journal of Aerospace Power,2014,29(1):14-22(in Chinese).
[10]朱呈祥,黄雨柔,陈荣钱,等.高超声速进气道的裂解碳氢燃料提前喷注研究[J].推进技术,2018,39(1):196-202.Zhu C X,Huang Y R,Chen R Q,et al.Pre-injection of cracked hydrocarbon fuel in hypersonic inlets[J].Journal of Propulsion Technology,2018,39(1):196-202(in Chinese).
[11]龚诚,孙明波,张顺平,等.超声速燃烧室氢气强迫点火过程实验[J].推进技术,2012,33(4):547-551.Gong C,Sun M B,Zhang S P,et al.Experimental study on the forced ignition of hydrogen in a supersonic combustor[J].Journal of Propulsion Technology,2012,33(4):547-551(in Chinese).
[12]杨浩,方祥军,林鹏,等.基于支板凹腔结构的超燃燃烧室数值研究[J].推进技术,2017,38(11):2555-2561.Yang H,Fang X J,Lin P,et al.Numerical study on strut/cavity-based scramjet combustor[J].Journal of Propulsion Technology,2017,38(11):2555-2561(in Chinese).
[13]黄思源,桂业伟,白菡尘,等.凹腔火焰稳定器回流区稳焰机理[J].推进技术,2011,32(5):684-689.Huang S Y,Gui Y W,Bai H C,et al.Flame stabilizing mechanism of recirculation-zone of cavity flameholder[J].Journal of Propulsion Technology,2011,32(5):684-689(in Chinese).
[14]胡欲立,刘欧子,蔡元虎,等.燃料喷射位置对凹槽火焰稳定特性的影响[J].空气动力学学报,2007,25(4):521-525.Hu Y L,Liu O Z,Cai Y H,et al.The effect of the different fuel injection on the cavity flame holding characteristic in kerosene supersonic combustion[J].Acta Aerodynamica Sinica,2007,25(4):521-525(in Chinese).
[15]Ben-Yakar A,Hanson R K.Cavity flame-holders for ignition and flame stabilization in scramjets:an overview[J].Journal of Propulsion and Power,2001,17(4):869-877.
[16]Mai T,Sakimitsu Y,Nakamura H,et al.Effect of the incident shock wave interacting with transversal jet flow on the mixing and combustion[J].Proceedings of the Combustion Institute,2011,33(2):2335-2342.
[17]王西耀,杨顺华,乐嘉陵.超燃冲压发动机带凹槽的燃烧室流场振荡研究[J].推进技术,2013,34(5):651-657.Wang X Y,Yang S H,Le J L.A study on flow oscillation in scramjet combustor with cavity[J].Journal of Propulsion Technology,2013,34(5):651-657(in Chinese).
[18]辜天来,张帅,郑耀.咽式进气道/等直隔离段的反压特性[J].浙江大学学报(工学版),2016,50(7):1418-1424.Gu T L,Zhang S,Zheng Y.Back pressure characteristics of jaws inlet with constant-area isolator[J].Journal of Zhejiang University(Engineering Science),2016,50(7):1418-1424(in Chinese).
[19]王成鹏,杨永阳,刘晨,等.超燃燃烧室流场计算方法比较分析[J].航空动力学报,2009,24(5):963-969.Wang C P,Yang Y Y,Liu C,et al.Comparative analysis of computational methods of supersonic combustor flowfield[J].Journal of Aerospace Power,2009,24(5):963-969(in Chinese).
[20]陈兵,龚春林,谷良贤.双模态超燃冲压发动机准一维流耦合方法与验证[J].推进技术,2018,39(4):731-739.Chen B,Gong C L,Gu L X.Analysis and verification of quasi one dimensional flow for dual mode scramjet[J].Journal of Propulsion Technology,2018,39(4):731-739(in Chinese).
[21]席文雄,孙明波,李庆.超声速气流中的斜激波诱导自点火[J].航空动力学报,2016,31(2):377-382.Xi W X,Sun M B,Li Q.Self-ignition in supersonic flow induced by oblique shock wave[J].Journal of Aerospace Power,2016,31(2):377-382(in Chinese).
[22]樊孝峰,王江峰,赵法明.Roe格式在多组元燃烧流场数值模拟中的应用[J].南京航空航天大学学报,2016,48(3):347-351.Fan X F,Wang J F,Zhao F M.Numerical simulation of multi-component reacting flow using Roe scheme[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(3):347-351(in Chinese).
[23]刘晨.复杂燃烧流场数值模拟方法研究[D].南京:南京航空航天大学,2009.Liu C.Numerical methods for complex combustion flowfields[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2009(in Chinese).
[24]Moretti G.A new technique for the numerical analysis of nonequilibrium flows[J].AIAA Journal,1965,3(2):223-229.
[25]赵法明,王江峰.高温空气化学反应流与多组元RCS热喷干扰流场数值模拟方法研究[C].第九届全国流体力学学术会议论文摘要集,南京,2016:1.Zhao F M,Wang J F.Numerical investigation of high temperature non-equilibrium flow and multi-components RCS jet interaction[C].Proceedings of the 9thNational Fluid Mechanics Conference,Nanjing,2016:1(in Chinese).
[26]Menter F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[27]田野,杨顺华,肖保国,等.空气节流对煤油燃料超燃燃烧室燃烧性能影响[J].宇航学报,2015,36(12):1421-1427.Tian Y,Yang S H,Xiao B G,et al.Effect of air throttling on combustion performance of a kerosene-fueled scramjet combustor[J].Journal of Astronautics,2015,36(12):1421-1427(in Chinese).
[28]胡如云,王亮,符松.后台阶流动及其控制述评[J].中国科学:物理学力学天文学,2015,45(12):44-53.Hu R Y,Wang L,Fu S.Review of backward-facing step flow and separation reduction[J].Scientia Sinica:Physica,Mechanica&Astronomica,2015,45(12):44-53(in Chinese).
[29]Segal C.The scramjet engine:processes and characteristics[M].Hardback:Cambridge University Press,2009.
[30]Baurle R,Mathur T,Gruber M,et al.A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications[C].Proceedings of the 34th AIAA/ASME//SAE/ASEE Joint Propulsion Conference and Exhibit,Joint Propulsion Conferences,Cleveland,OH,USA:AIAA,2013.