Numerical simulation of shock train oscillation flows caused by periodic throttle disturbances
-
摘要:
基于动网格方法数值模拟并分析来流马赫数为6，二元进气道/隔离段构型在频率为50～500 Hz周期节流下的激波串振荡流动。结果表明：当节流比在0.2～0.32范围内周期变化时，隔离段出现与节流频率相同的激波串振荡现象。节流频率会影响激波串振荡幅度和壁面压强波动特性。50 Hz与100 Hz工况的激波串流向振幅相近，100～500 Hz范围内随频率增加，流向振幅从15.5 mm减小至10.8 mm。壁面压强随频率的变化规律更加复杂，以凹腔中部为界，其上游壁面压强时均值、均方差峰值整体随频率增加而降低，其中50 Hz工况唇口侧壁面压强均方差峰值可达21倍来流静压，但其下游壁面压强无明显规律。分析表明节流频率对激波串振荡的影响与节流扰动的传播时间相关，工程设计中需综合考虑构型与反压参数对激波串振荡的影响。
Abstract:Based on the dynamic mesh method, the shock train oscillation flows of a two-dimensional inlet/isolator configuration caused by periodical throttle at frequencies from 50 to 500 Hz were investigated through numerical simulations under Mach number 6 freestream. The results showed that evident shock train oscillations appeared as the throttling ratio varied periodically within the range of (0.2−0.32), and the oscillation frequency accorded with the throttling disturbance frequency. The throttling frequency evidently affected the oscillation amplitude of the shock train and the characteristics of the wall pressure fluctuation. The oscillation ranges of shock train decreased with the increase of throttling frequency higher than or equal to 100 Hz, despite of the similar values between 50 Hz and 100 Hz conditions. The streamwise oscillation range was 15.5 mm and 10.8 mm under 100 Hz and 500 Hz conditions, respectively. Variation law of wall pressure with throttling frequency was complex. Time-averaged magnitudes and mean square deviations of the wall pressures decreased as the throttling frequency increased for the upstream section of the central part of cavity, while the variation laws of wall pressure were ambiguous for the downstream section. The highest square mean deviation was 21 times the freestream static pressure for the cowl sidewall pressure under 50 Hz condition. The analyses showed that variations of shock train oscillation with frequency were related to the response time of inlet/isolator flows to throttle disturbances. It is necessary to comprehensively consider the influences of configurations and back pressure parameters on shock train oscillation in engineering design.
-
Key words:
- hypersonic inlet /
- isolator /
- dynamic backpressure /
- shock train oscillation /
- fluctuating pressure
-
图 2 典型节流周期内堵塞比随时间变化曲线
Figure 2. Time histories of throttle ratio in a typical throttle period
图 7 时间步长无关性验证：典型壁面压强-时间曲线
Figure 7. Time step independence validation: typical wall pressure-time curves
图 10 周期节流工况典型测点压强-时间曲线（ f =100 Hz）
Figure 10. Time-pressure curves at typical monitoring point under the periodical throttle condition （ f =100 Hz）
图 11 典型时刻内流道流场（ f = 100 Hz）
Figure 11. Internal flowfiled at typical time instants （ f = 100 Hz）
图 12 激波串运动与壁面压强波动对比（ f = 100 Hz）
Figure 12. Comparison between shock train movement and wall pressure signals （ f = 100 Hz）
图 13 不同频率工况典型时刻隔离段流动云图
Figure 13. Isolator flowfield at typical flow instants with various frequencies
图 14 不同频率工况壁面压强时均值
Figure 14. Time- averaged magnitudes of wall pressure with various frequencies
图 15 不同频率工况壁面压强均方差
Figure 15. Standard deviations of wall pressure with various frequencies
图 16 典型工况振荡周期内壁面压强-时间规律
Figure 16. Wall pressures-time law for an oscillatory cycle under the typical conditions
图 17 不同增长时间工况凹腔侧壁面测点压强-时间曲线
Figure 17. Pressure-time curves of typical monitoring points on the cavity side wall under the various increase time conditions
表 1 数值模拟工况
Table 1. Numerical computation conditions
Tr, min Tr, max f/Hz 0.2 0.32 50, 100, 200, 320, 500 
下载: 导出CSV
表 2 自由来流参数
Table 2. Freestream flow parameters
参数 数值 来流马赫数 Ma∞ 5.9 来流静压 p∞/Pa 1050 来流静温 T∞/K 115 来流静密度 ρ∞/（kg/m3） 0.0318 来流速度 v∞/（m/s） 1268 来流单位雷诺数 （Re/L）/106 m−1 5.06
下载: 导出CSV
表 3 网格无关性验证参数
Table 3. Parameters of grid independence validation
网格 横向单元网格数目 流向单元网格数目 前体 内流道 前体 内流道 粗 260 140 384 624 密 320 175 480 780 加密 400 200 545 885
下载: 导出CSV
表 4 不同频率工况激波⑧流向振荡范围
Table 4. Streamwise oscillation range and shock ⑧ position with various frequency
f/Hz xmin/m xmax/m Ax/mm 50 0.3970 0.4122 15.2 100 0.3964 0.4119 15.5 200 0.3961 0.4100 13.9 320 0.3995 0.4121 12.6 500 0.4010 0.4118 10.8
下载: 导出CSV
表 5 不同频率工况激波⑧波脚流向坐标参数
Table 5. Streamwise coordinate parameters of foot of shock ⑧ with various frequencies
f/Hz xave/mm xσmax/mm 50100200320500 404.24404.44404.21406.59407.06 410.12409.02405.76409.91409.38
下载: 导出CSV
-
[1] MATSUO K,MIYAZATO Y,KIM H D. Shock train and pseudo-shock phenomena in internal gas flows[J]. Progress in Aerospace Sciences,1999,35(1): 33-100. doi: 10.1016/S0376-0421(98)00011-6 [2] LAURENCE S J,LIEBER D,MARTINEZ S J,et al. Incipient thermal choking and stable shock train formation in the heat release region of a scramjet combustor: Part Ⅰ shock-tunnel experiments[J]. Combustion and Flame,2015,162(4): 921-931. doi: 10.1016/j.combustflame.2014.09.016 [3] HUNT R L,GAMBA M. Shock train unsteadiness characteristics, oblique to normal transition, and three-dimensional leading shock structure[J]. AIAA Journal,2018,56(4): 1569-1587. doi: 10.2514/1.J056344 [4] VANSTONE L,HASHEMI K E,LINGREN J,et al. Closed loop control of shock-train location in a combusting scramjet[J]. Journal of Propulsion and Power,2018,34(3): 660-667. doi: 10.2514/1.B36743 [5] RILEY L P,GAITONDE D V,HAGENMAIER M A,et al. Isolator dynamics during unstart of a dual-mode scramjet[J]. Journal of Propulsion and Power,2018,34(6): 1-19. [6] TAN Huijun,LI Liugang,WEN Yufen,et al. Experimental investigation of the unstart process of a generic hypersonic inlet[J]. AIAA Journal,2011,49(2): 279-288. doi: 10.2514/1.J050200 [7] 徐珂靖,常军涛,李楠,等. 背景波系下的隔离段激波串运动特性及其流动机理研究进展[J]. 实验流体力学,2019,33(3): 31-42. doi: 10.11729/syltlx20180196XU Kejing,CHANG Juntao,LI Nan,et al. Recent research progress on motion characteristics and flow mechanism of shock train in an isolator with back groundwaves[J]. Journal of Experiments in Fluid Mechanics,2019,33(3): 31-42. (in Chinese) doi: 10.11729/syltlx20180196 [8] HUNT R L,GAMBA M. On the origin and propagation of perturbations that cause shock train inherent unsteadiness[J]. Journal of Fluid Mechanics,2019,861: 815-859. doi: 10.1017/jfm.2018.927 [9] FIEVET R,KOO H,RAMAN V,et al. Numerical investigation of shock-train response to inflow boundary layer variations[J]. AIAA Journal,2017,55(9): 2888-2901. doi: 10.2514/1.J055333 [10] XIONG Bing,FAN Xiaoqiang,WANG Yi,et al. Experimental study on self-excited and forced oscillations of an oblique shock train[J]. Journal of Spacecraft and Rockets,2018,55(3): 640-647. doi: 10.2514/1.A33973 [11] 黄蓉,李祝飞,聂宝平,等. 带抽吸二元进气道/隔离段激波串振荡特性[J]. 推进技术,2020,41(4): 767-777. doi: 10.13675/j.cnki.tjjs.190121HUANG Rong,LI Zhufei,NIE Baoping,et al. Shock train oscillations in a two-dimensional inlet/isolator with suction[J]. Journal of Propulsion Technology,2020,41(4): 767-777. (in Chinese) doi: 10.13675/j.cnki.tjjs.190121 [12] SU Weiyi,CHEN Yun,ZHANG Fengrui,et al. Control of pseudo-shock oscillation in scramjet inlet-isolator using periodical excitation[J]. Acta Astronautica,2018,143: 147-154. doi: 10.1016/j.actaastro.2017.10.040 [13] 苏纬仪,王赫,陈云,等. 壁温对隔离段激波串振荡的影响[J]. 航空动力学报,2017,32(7): 1605-1612. doi: 10.13224/j.cnki.jasp.2017.07.010SU Weiyi,WANG He,CHEN Yun,et al. Effects of wall temperature on pseudoshock oscillations in isolator[J]. Journal of Aerospace Power,2017,32(7): 1605-1612. (in Chinese) doi: 10.13224/j.cnki.jasp.2017.07.010 [14] 孙斐,苏纬仪,侯强,等. 进气道激波串振荡的模态分解及快速预测[J]. 航空动力学报,2021,36(5): 1040-1051. doi: 10.13224/j.cnki.jasp.2021.05.015SUN Fei,SU Weiyi,HOU Qiang,et al. Modal decomposition and rapid prediction of shock train oscillation for inlet[J]. Journal of Aerospace Power,2021,36(5): 1040-1051. (in Chinese) doi: 10.13224/j.cnki.jasp.2021.05.015 [15] 李一鸣, 李祝飞, 杨基明, 等. 隔离段横向喷流作用下激波串运动特性研究[J]. 实验流体力学, 2018, 32(5): 1- 6.LI Yiming, LI Zhufei, YANG Jiming, et al. Characteristics of the shock train motions caused by transverse injections into the isolator[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 1- 6. (in Chinese) [16] SU Weiyi,JI Yuxuan,CHEN Yun. Effects of dynamic backpressure on pseudoshock oscillations in scramjet inlet-isolator[J]. Journal of Propulsion and Power,2016,32(2): 1-13. [17] XIONG Bing,FAN Xiaoqiang,WANG Zhenguo,et al. Analysis and modelling of unsteady shock train motions[J]. Journal of Fluid Mechanics,2018,846: 240-262. doi: 10.1017/jfm.2018.209 [18] WANG Chengpeng,CHENG Chuan,CHENG Keming. Unsteady behavior of oblique shock train and boundary layer interactions[J]. Aerospace Science and Technology,2018,79: 212-222. doi: 10.1016/j.ast.2018.05.054 [19] CHENG Chuan,WANG Chengpeng,CHENG Keming. Response of an oblique shock train to downstream periodic pressure perturbations[J]. Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering,2019,233(1): 57-70. doi: 10.1177/0954410017727028 [20] LI Nan,CHANG Juntao,XU Kejing,et al. Oscillation of the shock train in an isolator with incident shocks[J]. Physics of Fluids,2018,30(11): 116102.1-116102.20. [21] LI Nan,CHANG Juntao,XU Kejing,et al. Instability of shock train behaviour with incident shocks[J]. Journal of Fluid Mechanics,2021,907: A40.1-A40.27. [22] 詹王杰,严红. 隔离段内激波串受稳态和脉动背压影响的数值研究[J]. 推进技术,2021,42(5): 980-990. doi: 10.13675/j.cnki.tjjs.190671ZHAN Wangjie,YAN Hong. Numerical study of effects of steady and oscillating back-pressure on shock train in an isolator[J]. Journal of Propulsion Technology,2021,42(5): 980-990. (in Chinese) doi: 10.13675/j.cnki.tjjs.190671 [23] 蔡建华, 周进, 刘世杰, 等. 脉动反压波形对激波串运动特性的影响[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: 发动机内流气动技术. 辽宁 大连: 中国航天第三专业信息网, 2017: 264-273. [24] 李季,罗佳茂,杨顺华. 边界层抽吸和脉动反压作用下隔离段内流动特性研究[J]. 推进技术,2019,40(8): 1759-1766.LI Ji,LUO Jiamao,YANG Shunhua. A study of flow characteristics in isolator with effects of boundary layer suction and oscillating back pressure[J]. Journal of Propulsion Technology,2019,40(8): 1759-1766. (in Chinese) [25] NIE Baoping, LI Zhufei, HUANG Rong, et al. Effect of boundary layer suction on shock train oscillations in an inlet/isolator model[C]//Proceedings of the 32nd International Symposium on Shock Waves. Singapore: International Shock Wave Institute, 2019: 719-728. [26] LI Zhufei,GAO Wenzhi,JIANG Hongliang,et al. Unsteady behaviors of a hypersonic inlet caused by throttling in shock tunnel[J]. AIAA Journal,2013,51(10): 2485-2492. doi: 10.2514/1.J052384 [27] LIN K C,JACKSON K,BEHDADNIA R,et al. Acoustic characterization of an ethylene-fueled scramjet combustor with a cavity flameholder[J]. Journal of Propulsion and Power,2010,26(6): 1161-1169. doi: 10.2514/1.43338 [28] WANG Zhenguo,SUN Mingbo,WANG Hongbo,et al. Mixing-related low frequency oscillation of combustion in an ethylene-fueled supersonic combustor[J]. Proceedings of the Combustion Institute,2015,35(2): 2137-2144. doi: 10.1016/j.proci.2014.09.005 [29] GAO Wenzhi,CHEN Jian,LIU Changhai,et al. Effects of vortex generators on unsteady unstarted flows of an axisymmetric inlet with nose bluntness[J]. Aerospace Science and Technology,2020,104: 106021.1-106021.15. [30] ANSYS Inc. ANSYS fluent users guide release 18.0, chapter 10: modeling flows using sliding and dynamic meshes[R]. Canonsburg, US: ANSYS, Inc. , 2017. [31] 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 [32] IZUMI K,ASO S,NISHIDA M. Experimental and computational studies focusing processes of shock waves reflected from parabolic reflectors[J]. Shock Waves,1994,3(3): 213-222. doi: 10.1007/BF01414715 [33] SMITS A J, DUSSUAGE J P. Turbulent shear layers in supersonic flow [M]. New York: Springer, 1996. -
点击查看大图
计量
- 文章访问数: 500
- HTML浏览量: 470
- PDF量: 65
- 被引次数: 0