边界层抽吸和脉动反压作用下隔离段内流动特性研究

doi:10.13675/j.cnki. tjjs. 180498

推进技术 ›› 2019, Vol. 40 ›› Issue (8): 1759-1766.DOI: 10.13675/j.cnki. tjjs. 180498

边界层抽吸和脉动反压作用下隔离段内流动特性研究

1.中国空气动力研究与发展中心空气动力学国家重点实验室;2.中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室

发布日期:2021-08-15
基金资助:
空气动力学国家重点实验室研究基金 JBKY17060603空气动力学国家重点实验室研究基金（JBKY17060603）。

A Study of Flow Characteristics in Isolator with Effects ofBoundary Layer Suction and Oscillating Back Pressure

1.State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center，Mianyang 621000,China;2.Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute，CARDC, Mianyang 621000,China

Published:2021-08-15

摘要/Abstract

摘要： 为了解上游边界层抽吸控制和下游周期脉动反压作用下隔离段内流动特性，采用非定常数值模拟和理论分析相结合的方法，对来流Ma=2情况下的隔离段内激波串动态演化特性、激波串形态结构变化以及激波串演化迟滞现象进行了研究。结果表明，在脉动反压和边界层抽吸作用下，激波串在上游抽吸狭缝与下游隔离段出口之间周期振荡，振荡频率与脉动反压一致。在振荡过程中，首道激波串形态在规则反射与马赫反射以及马赫反射与弧形激波（包含正激波）之间相互转换。边界层抽吸将激波串固定在抽吸狭缝位置，有效提高了隔离段抗反压性能，脉动频率越大，可承受的瞬态反压峰值越大。在一个振荡周期内，激波串向上移动速度较向下移动更快，且在上下移动过程中形态变化存在迟滞现象。

关键词: 边界层抽吸;脉动反压;激波串;迟滞现象;隔离段

Abstract: To investigate the flow characteristics in the isolator influenced by the boundary layer suction at upstream and the oscillating back pressure at downstream, unsteady numerical simulation and theoretical analysis methods are used to study the shock train dynamic evolution, the structure variation and the hysteresis as the upstream flow condition is Ma=2. Results show that the boundary layer suction and oscillating back pressure can induce the shock train oscillating periodically between the suction position and the isolator outlet, and the oscillation frequency is identical to the back pressure frequency. During an oscillation process, the first shock train varies between a regular reflection and a Mach reflection or between a Mach reflection and an arc shock (including a normal shock). Besides, the boundary layer suction impels the shock train fixed at the suction slot, which effectively improves the resistance capability of the isolator to the back pressure, and the peak value of the back pressure increases as the oscillation frequency increases. Results as well exhibit that during an oscillation period, the shock train moves upwards faster than downwards, and a hysteresis for the shock structure occurs as the shock train moves up and down.

Key words: Boundary layer suction;Oscillating back pressure;Shock train;Hysteresis phenomenon;Isolator

. 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.

参考文献

[1] Matsuo K, Miyazato Y， Kim H. Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows[J]. Progress in Aerospace Sciences， 1999， 35(1): 33-100.
[2] 李博，梁德旺. 高超声速进气道-隔离段反压引起不起动计算[J]. 推进技术， 2006， 27(5): 431-435. (LI Bo， LIANG De-wang. Calculation of Unstarted Flow in Hypersonic Inlet-Isolator with High Back Pressure[J]. Journal of Propulsion Technology， 2006， 27(5): 431-435.)
[3] 金亮，吴先宇，罗世彬，等. 隔离段反压对激波串起始位置的影响[J]. 推进技术， 2008， 29(1): 54-57.
[4] Yu K， Pang B， Hsu O. Implementing Active Combustion Control in Propulsion Systems[R]. AIAA2001-3849.
[5] Ma F H， Li J， Yang V. Thermo Acoustic Flow Instability in a Scramjet Combustor[R]. AIAA2005-3824.
[6] Lin K C， Ma F H， Li J， et al. Acoustic Characterization of an Ethylene-Fueled Scramjet Combustor with a Recessed Cavity Flame Holder[R]. AIAA2007-5382.
[7] Lin K C， Jackson K， Behdadnia R， et al. Acoustic Characterization of an Ethylene-Fueled Scramjet Combustor with a Cavity Flame Holder[J]. Journal of Propulsion and Power， 2010， 26(6): 1161-1169.
[8] Morris M J， Sajben M， and Kroutil J C. Experimental Investigation of Normal Shock/Turbulent Boundary Layer Interactions with and Without Mass Removal[J]. AIAA Journal， 1992， 30(2): 359-366.
[9] Harloff G J， and Smith G E. Supersonic-Inlet Boundary-Layer Bleed Flow[R]. NASA-CR-195426， 1995.
[10] Tindell R， and Willis B. Experimental Investigation of Blowing for Controlling Oblique Shock/Boundary Layer Interactions[R]. AIAA97-2642.
[11] Delery J M. Shock Wave/Turbulent Boundary Layer Interaction and Its Control[J]. Progress in Aerospace Sciences， 1985， 22(4): 209-280.
[12] McCormick D C. Shock/Boundary-Layer Interaction Control with Vortex Generators and Passive Cavity[J]. AIAA Journal， 1993， 31(1): 91-96.
[13] 陈逖，高超声速进气道内激波/边界层干扰及射流式涡流发生器的流动控制方法研究[D]. 长沙：国防科技大学， 2011.
[14] Chyu W J， Rimlinger M J， Shih T P. Control of Shock-Wave Boundary-Layer Interactions by Bleed[J]. AIAA Journal， 1995， 33(7): 1239-1247.
[15] Weiss A， Grzona A， Olivier H. Behavior of Shock Trains in a Diverging Duct[J]. Experiments in Fluids， 2010， 49(2): 355-365.
[16] Weiss A， Olivier H. Shock Boundary Layer Interaction under the Influence of a Normal Suction Slot[J]. Shock Waves， 2014， 24(1): 11-19.
[17] 马生虎，岳连捷，贾轶楠，等. 隔离段抽吸引起的激波迟滞现象研究[J]. 推进技术， 2017， 38(4): 732-739.
[18] 曹学斌，张堃元. 超燃冲压发动机隔离段非对称来流下激波串受迫振荡流动研究[J]. 空气动力学学报， 2011， 29(2): 135-141.
[19] 曹学斌. 矩形隔离段流动特性及控制规律研究[D]. 南京：南京航空航天大学， 2011.
[20] 田旭昂，王成鹏，程克明. Ma5斜激波串动态特性实验研究[J]. 推进技术， 2014， 35(8): 1030-1039. (TIAN Xu-ang， WANG Cheng-peng， CHENG Ke-ming. Experimental Investigation of Dynamic Characteristics of Oblique Shock Train in Mach 5 Flow[J]. Journal of Propulsion Technology， 2014， 35(8): 1030-1039.)
[21] 熊冰，王振国，范晓樯，等. 隔离段内正激波串受迫振荡特性研究[J]. 推进技术， 2017， 38(1): 1- 7.
[22] 赵慧勇. 超燃冲压整体发动机并行数值研究[D]. 绵阳：中国空气动力研究与发展中心， 2005.
[23] 田野，乐嘉陵，杨顺华，等. 乙烯燃料超燃冲压发动机流场振荡及其控制研究[J]. 推进技术， 2015， 36(7): 961-967.
[24] 何粲，邢建文，肖保国，等. 反压对隔离段激波串结构的影响[J]. 航空动力学报， 2016， 31(5): 1243-1251.
[25] Yu K， Pang B， Hsu O. Implementing Active Combustion Control in Propulsion Systems[R]. AIAA2001-3849
[26] Chapman D R， Kuehn D M， Larson H K. Investigation of Separated Flows in Supersonic and Subsonic Streams with Emphasis on the Effect of Transition[R]. NACA Report 1356， 1958.
[27] Von Neumann J. Refraction， Intersection and Reflection of Shock Waves[R]. Navord Report 203-45， 1945.
[28] Tao Y， Fan X Q， Zhao Y L. Viscous Effects of Shock Reflection Hysteresis in Steady Supersonic Flows[J]. Journal of Fluid Mechanics， 2014， 759(1): 134-148.

边界层抽吸和脉动反压作用下隔离段内流动特性研究

A Study of Flow Characteristics in Isolator with Effects ofBoundary Layer Suction and Oscillating Back Pressure

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价