Numerical simulation of mixing and combustion performance of pulsed injection in a kerosene-fueled scramjet
-
摘要: 为研究脉冲喷注对超燃冲压发动机气态煤油混合及燃烧性能的影响，采用二维雷诺平均方程及两方程剪切应力输运模型进行数值模拟，探究了以双凹腔超燃冲压发动机模型在入口马赫数2.5、总压1.75 MPa、总温1350 K条件下的流场结构。对比分析了定常喷注和脉冲喷注下煤油与空气的混合和燃烧性能。研究结果表明：数值模拟纹影图与试验结果吻合较好，出现对应纹影仅先于试验0.2 ms，占一个流场振荡周期（6.9 ms）的2.89%。研究发现：在脉冲喷注工况下，回流区在流场振荡周期内能持续更长时间，延长了燃料在凹腔内的滞留时间；未发现脉冲喷注对总压损失有显著贡献，但脉冲喷注工况下温度与压力分布均匀，不会出现热力学喉道。Abstract: To investigate the impact of gaseous kerosene on the mixing and combustion performance of a scramjet combustor with pulsed injection, the two-dimensional RANS equations are solved using the two-equation k–ω SST turbulence model. The flow field structure of the scramjet model with the cavity and backward step as the flame stabilizer under the condition of Mach 2.5 inflow, total pressure of 1.75 MPa, and total temperature of 1350 K is investigated. The mixing and combustion performance of kerosene and air under steady injection and pulsed injection are compared and analyzed. The results show that the simulated schlieren pattern is in good agreement with the test, only 0.2 ms earlier than the test, accounting for 2.89% of an oscillation period (6.9 ms). Pulsed injection results in a prolonged existence of the recirculation zone within the combustion chamber cavity, enhancing fuel retention in this region. It is not found that the pulsed injection has a significant contribution to the total pressure loss, while the temperature and pressure distribution of the pulsed injection is uniform without the thermo-dynamic throat.
-
图 4 试验与数值模拟冷流流场对比
Figure 4. Comparison of experimental and simulated cold flow fields upstream
图 5 试验及数值模拟上壁面压力图
Figure 5. Experimental and numerical simulation of upper wall pressure
图 6 燃烧室上游流线和压力等值线图
Figure 6. Streamlines and pressure isogram of the combustion chamber
图 7 定常喷注煤油的摩尔分数分布及流线图
Figure 7. Steady injection kerosene mole fraction and streamline diagram
图 8 脉冲喷注煤油的摩尔分数分布及流线图
Figure 8. Pulsed injection kerosene mole fraction and streamline diagram
表 1 边界条件
Table 1. Boundary condition
pt/kPa p0/Pa T/K Inlet 1750 102423 1350 Jet 1500 79239 300 
下载: 导出CSV
-
[1] URZAY J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight[J]. Annual Review of Fluid Mechanics, 2018, 50: 593–627. doi: 10.1146/annurev-fluid-122316-045217 [2] LIU Q L, BACCARELLA D, LEE T H. Review of combustion stabilization for hypersonic airbreathing propulsion[J]. Progress in Aerospace Sciences, 2020, 119: 100636. doi: 10.1016/j.paerosci.2020.100636 [3] ZUO Q R, YU H L, DAI J. Effects of cavity-induced mixing enhancement under oblique shock wave interference: numerical study[J]. International Journal of Hydrogen Energy, 2021, 46(72): 35706–35717. doi: 10.1016/j.ijhydene.2021.08.131 [4] BARZEGAR GERDROODBARY M, RAHIMI TAKAMI M, HEIDARI H R, et al. Comparison of the single/multi transverse jets under the influence of shock wave in supersonic crossflow[J]. Acta Astronautica, 2016, 123: 283–291. doi: 10.1016/j.actaastro.2016.03.031 [5] SHARMA V, ESWARAN V, CHAKRABORTY D. Effect of location of a transverse sonic jet on shock augmented mixing in a SCRAMJET engine[J]. Aerospace Science and Technology, 2020, 96: 105535. doi: 10.1016/j.ast.2019.105535 [6] 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. doi: 10.1016/j.proci.2010.07.056 [7] HUANG W, WU H, DU Z B, et al. Design exploration on the mixing augmentation induced by the oblique shock wave and a novel step in a supersonic flow[J]. Acta Astronautica, 2021, 180: 622–629. doi: 10.1016/j.actaastro.2020.12.058 [8] TRETYAKOV P K. Organization of a pulsed mode of combustion in scramjets[J]. Combustion, Explosion, and Shock Waves, 2012, 48(6): 677–682. doi: 10.1134/S0010508212060020 [9] SHI H T, WANG G L, LUO X S, et al. Large-eddy simulation of a pulsed jet into a supersonic crossflow[J]. Computers & Fluids, 2016, 140: 320–333. doi: 10.1016/j.compfluid.2016.10.009 [10] CHEN S, ZHAO D. RANS investigation of the effect of pulsed fuel injection on scramjet HyShot II engine[J]. Aerospace Science and Technology, 2019, 84: 182–192. doi: 10.1016/j.ast.2018.10.022 [11] DU Z B, HUANG W, YAN L, et al. Reynolds-average Navier-Stokes study of steady and pulsed gaseous jets with different periods for the shock-induced combustion ramjet engine[J]. Physics of Fluids, 2019, 31(5): 055107. doi: 10.1063/1.5097238 [12] DU Z B, HUANG W, YAN L, et al. RANS study of steady and pulsed gaseous jets into a supersonic crossflow[J]. International Journal of Heat and Mass Transfer, 2019, 136: 157–169. doi: 10.1016/j.ijheatmasstransfer.2019.02.103 [13] MILLER W A, MEDWELL P R, DOOLAN C J, et al. Numerical investigation of a pulsed reaction control jet in hypersonic crossflow[J]. Physics of Fluids, 2018, 30(10): 106108. doi: 10.1063/1.5048544 [14] DAI J, ZUO Q R. Numerical investigation on mixing enhancement of the cavity with pulsed jets under oblique shock wave interference[J]. Aerospace Science and Technology, 2022, 123: 107454. doi: 10.1016/j.ast.2022.107454 [15] ZHAO M J, LI Q L, YE T H. Investigation of an optimal pulsed jet mixing and combustion in supersonic crossflow[J]. Combustion and Flame, 2021, 227: 186–201. doi: 10.1016/j.combustflame.2021.01.005 [16] WILLIAMS N J, MOELLER T M, THOMPSON R J. Numerical simulations of high frequency transverse pulsed jet injection into a supersonic crossflow[J]. Aerospace Science and Technology, 2020, 103: 105908. doi: 10.1016/j.ast.2020.105908 [17] HE Z, TIAN Y, LE J L, et al. Effects of pulsed injection on ignition delay and combustion performance in a hydrogen-fuel scramjet combustor[J]. Acta Astronautica, 2022, 193: 152–162. doi: 10.1016/j.actaastro.2022.01.012 [18] TIAN Y, GUO M M, RAN W, et al. Experimental investigation of effects of pulsed injection on flow structure and flame development in a kerosene-fueled scramjet with pilot hydrogen[J]. Physics of Fluids, 2022, 34(5): 055109. doi: 10.1063/5.0094932 [19] BARZEGAR GERDROODBARY M, JAHANIAN O, MOKHTARI M. Influence of the angle of incident shock wave on mixing of transverse hydrogen micro-jets in supersonic crossflow[J]. International Journal of Hydrogen Energy, 2015, 40(30): 9590–9601. doi: 10.1016/j.ijhydene.2015.04.107 [20] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598–1605. doi: 10.2514/3.12149 [21] HUANG S Z, CHEN Q. Numerical evaluation of shock wave effects on turbulent mixing layers in a scramjet combustor[J]. Case Studies in Thermal Engineering, 2021, 25: 100893. doi: 10.1016/j.csite.2021.100893 [22] HUANG W, WANG Z G, WU J P, et al. Numerical prediction on the interaction between the incident shock wave and the transverse slot injection in supersonic flows[J]. Aerospace Science and Technology, 2013, 28(1): 91–99. doi: 10.1016/j.ast.2012.10.007 [23] BARZEGAR GERDROODBARY M, GANJI D D, AMINI Y. Numerical study of shock wave interaction on transverse jets through multiport injector arrays in supersonic crossflow[J]. Acta Astronautica, 2015, 115: 422–433. doi: 10.1016/j.actaastro.2015.06.002 [24] DU Z B, SHEN C B, HUANG W, et al. Mixing augmentation induced by the combination of the oblique shock wave and secondary recirculation jet in a supersonic crossflow[J]. International Journal of Hydrogen Energy, 2022, 47(11): 7458–7477. doi: 10.1016/j.ijhydene.2021.12.069 [25] LI Z X, DINH MANH T, BARZEGAR GERDROODBARY M, et al. The influence of the wedge shock generator on the vortex structure within the trapezoidal cavity at supersonic flow[J]. Aerospace Science and Technology, 2020, 98: 105695. doi: 10.1016/j.ast.2020.105695 [26] HUANG W, LIU W D, LI S B, et al. Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows[J]. Acta Astronautica, 2012, 73: 1–9. doi: 10.1016/j.actaastro.2011.12.003 [27] ZHA Z M, YE Z Y, HONG Z, et al. Effects of unsteady oblique shock wave on mixing efficiency of two-dimensional supersonic mixing layer[J]. Acta Astronautica, 2021, 178: 60–71. doi: 10.1016/j.actaastro.2020.07.028 -
点击查看大图
图(12) / 表(1)
计量
- 文章访问数: 73
- HTML全文浏览量: 43
- PDF下载量: 7
- 被引次数: 0
