Characteristics of the shock train motions caused by transverse injections into the isolator
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摘要: 在马赫数6的激波风洞中，通过隔离段壁面处的横向喷流控制隔离段反压，借助高速纹影和壁面静压测量，研究了二元进气道/隔离段内激波串运动特性。结果表明：进气道起动后，流场中的反射波系构成了背景激波；开启横向喷流后，隔离段下游气流不断蓄积使得反压升高，隔离段内出现激波串。在反压作用下，激波串逐渐前移，其前沿激波的形态和前移速度受上游背景激波的影响而发生变化；背景激波入射壁面的区域自身存在较强的逆压梯度，能够增强与入射点同侧的前沿激波分支，使得前沿激波急剧前移。前沿激波被推出隔离段后，在进气道肩点附近短暂振荡，反压进一步增大后，进气道不起动并出现喘振。关闭喷流使反压降低后，进气道再起动。Abstract: Characteristics of the shock train motions in a two-dimensional inlet/isolator were investigated in a shock tunnel with a nominal Mach number of 6. The backpressure that supported the shock train was well controlled by using transverse injections into the isolator. High-speed schlieren and wall pressure measurements were carried out. Results show that the reflected shock waves in the inlet/isolator started flow form the background shock waves. As the transverse injections are opened, the downstream flow is accumulated with the increase of the backpressure and the induce of the shock train in the isolator. When the shock train moves upstream under the influence of the high backpressure, the shape and intensity of the leading shock in the shock train are changed by the background shock waves. Because strong adverse pressure gradients already exist near the incident points of the background shock waves, the leading shock of the shock train at the same side would be enhanced for moving upstream quickly. As the shock train is expelled out of the isolator, the leading shock oscillates near the shoulder for a short duration, until the backpressure is increased further to initiate the inlet buzz. When the backpressure is reduced by switching off the transverse injections, the inlet restarts.
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Key words:
- shock train /
- transverse injection /
- shock tunnel /
- two-dimensional inlet /
- high-speed schlieren
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图 5 对称面数值纹影和壁面压强
Figure 5. Numerical schlieren on the symmetry plane and wall pressure
图 8 激波串在背景激波入射点附近的纹影
Figure 8. Schlieren of the shock train near the incident point of the background shock
图 9 背景流场逆压梯度分布示意图
Figure 9. Schematic of adverse pressure gradient in the background flow field
图 10 激波串在肩点附近振荡时纹影
Figure 10. Schlieren of the shock train oscillating near the shoulder
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[1] Heiser W H, Pratt D T, Daley D H, et al. Hypersonic airbreathing propulsion[M]. Reston, VA:AIAA, 1994. [2] Waltrup P J, Billig F S. Structure of shock waves in cylindrical ducts[J]. AIAA Journal, 1973, 11(10):1404-1408. doi: 10.2514/3.50600 [3] Billig F S. Research on supersonic combustion[J]. Journal of Propulsion and Power, 1999, 9(4):499-514. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201608024 [4] Smart M K. Flow modeling of pseudoshocks in backpressured ducts[J]. AIAA Journal, 2015, 53(12):3577-3588. doi: 10.2514/1.J054021 [5] Shapiro A H. The dynamics and thermodynamics of compressible fluid flow[M]. New York:Wiley, 1953. [6] 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. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201707010Su W Y, Wang H, Chen Y, et al. Effects of wall temperature on pseudo-shock oscillations in isolator[J]. Journal of Aerospace Power, 2017, 32(7):1605-1612. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201707010 [7] 马广甫, 谢文忠, 林宇, 等.二元超声速进气道扩张段内伪激波特性[J].航空动力学报, 2017, 32(8):1950-1961. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201708019Ma G F, Xie W Z, Lin Y, et al. Pseudo-shock characteristics in the two-dimensional supersonic inlet diffuser[J]. Journal of Aerospace Power, 2017, 32(8):1950-1961. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201708019 [8] Huang H X, Tan H J, Sun S, et al. Behavior of shock train in curved isolators with complex background waves[J]. AIAA Journal, 2017, 56(1):1-13. http://cn.bing.com/academic/profile?id=438d0e13d1d367f364e3216031f6e0f3&encoded=0&v=paper_preview&mkt=zh-cn [9] Xu K J, Chang J T, Zhou W X, et al. Mechanism of shock train rapid motion induced by variation of attack angle[J]. Acta Astronautica, 2017, 140:18-26. doi: 10.1016/j.actaastro.2017.08.009 [10] Li N, Chang J T, Xu K J, et al. Prediction dynamic model of shock train with complex background waves[J]. Physics of Fluids, 2017, 29(11):116103. doi: 10.1063/1.5000876 [11] 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. http://d.old.wanfangdata.com.cn/Periodical/tjjs201701001Xiong B, Wang Z G, Fan X Q, et al. Characteristics of forced normal shock-train oscillation in isolator[J]. Journal of Propulsion Technology, 2017, 38(1):1-7. http://d.old.wanfangdata.com.cn/Periodical/tjjs201701001 [12] 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. http://d.old.wanfangdata.com.cn/Periodical/tjjs201408004Tian X A, Wang C P, Cheng K M. Experimental investigation of dynamic characteristics of oblique shock train in Mach 5 flow[J]. Journal of Propulsion Technology, 2014, 35(8):1030-1039. http://d.old.wanfangdata.com.cn/Periodical/tjjs201408004 [13] Tan H J, Li L G, Wen Y F, et al. Experimental investigation of the unstart process of a generic hypersonic inlet[J]. AIAA Journal, 2011, 42(2):279-288. http://cn.bing.com/academic/profile?id=07632c8aaa031462506568ca4882670f&encoded=0&v=paper_preview&mkt=zh-cn [14] Li N, Chang J T, Yu D R, et al. Mathematical model of shock-train path with complex background waves[J]. Journal of Propulsion and Power, 2016, 33(2):468-478. http://cn.bing.com/academic/profile?id=abd32ddb63b6023977c23c747987d7ba&encoded=0&v=paper_preview&mkt=zh-cn [15] Xu K J, Chang J T, Zhou W X, et al. Mechanism and prediction for occurrence of shock-train sharp forward movement[J]. AIAA Journal, 2016, 54(1):1403-1412. http://cn.bing.com/academic/profile?id=65f756e400b39cf125c82f075c0b319e&encoded=0&v=paper_preview&mkt=zh-cn [16] 浮强, 宋文艳, 韩小宝, 等.双模态燃烧室隔离段激波串位置的测量及控制[J].航空计算技术, 2017, 47(2):20-24. doi: 10.3969/j.issn.1671-654X.2017.02.006Fu Q, Song W Y, Han X B, et al. Dual-mode scramjet isolator shock train leading edge measurement and control[J]. Aeronautical Computing Technique, 2017, 47(2):20-24. doi: 10.3969/j.issn.1671-654X.2017.02.006 [17] Ridings A N, Smart M K. Flow establishment of precombustion shock trains in a shock tunnel[J]. AIAA Journal, 2017, 55(9):2902-2911. doi: 10.2514/1.J055590 [18] Chang J T, Li N, Xu K J, et al. Recent research progress on unstart mechanism, detection and control of hypersonic inlet[J]. Progress in Aerospace Sciences, 2017, 89:1-22. doi: 10.1016/j.paerosci.2016.12.001 [19] Gnani F, Zare-Behtash H, Kontis K. Pseudo-shock waves and their interactions in high-speed intakes[J]. Progress in Aerospace Sciences, 2016, 82:36-56. doi: 10.1016/j.paerosci.2016.02.001 [20] Do H, Im S K, Mungal M G, et al. The Influence of boundary layers on supersonic inlet flow unstart induced by mass injection[J]. Experiments in Fluids, 2011, 51(3):679-691. doi: 10.1007/s00348-011-1077-3 [21] 李祝飞, 高文智, 李鹏, 等.二元高超声速进气道激波振荡特性实验[J].推进技术, 2012, 33(5):676-682. http://d.old.wanfangdata.com.cn/Periodical/tjjs201205003Li Z F, Gao W Z, Li P, et al. Experimental investigation on the shock wave oscillation behaviors in a two-dimensional hypersonic inlet flow[J]. Journal of Propulsion Technology, 2012, 33(5):676-682. http://d.old.wanfangdata.com.cn/Periodical/tjjs201205003 [22] Li Z F, Gao W Z, Jiang H L, 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 [23] 李祝飞, 高文智, 杨基明.一种二元进气道起动特性的数值与实验考察[J].推进技术, 2016, 37(7):1224-1232. http://d.old.wanfangdata.com.cn/Periodical/tjjs201607004Li Z F, Gao W Z, Yang J M. Numerical and experimental investigation for starting characteristics of a two-dimensional inlet[J]. Journal of Propulsion Technology, 2016, 37(7):1224-1232. http://d.old.wanfangdata.com.cn/Periodical/tjjs201607004 -
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