考虑进气道喉道非均匀流场影响的隔离段直连试验

推进技术 ›› 2015, Vol. 36 ›› Issue (4): 547-555.

考虑进气道喉道非均匀流场影响的隔离段直连试验

曹学斌¹,朱守梅¹,满延进¹,易仕和²,陈植²

北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,国防科技大学航天与材料工程学院，湖南长沙 410073,国防科技大学航天与材料工程学院，湖南长沙 410073

发布日期:2021-08-15
作者简介:曹学斌( 1984—)，男，博士，工程师，研究领域为内流气体动力学。

DirectionConnectTestonIsolatorConsideringEffectsof NonuniformFlowatInletThroat

State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute，Beijing 100074，China,State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute，Beijing 100074，China,State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute，Beijing 100074，China,College of Aerospace and Material Technology，National University of Defence Technology，Changsha 410073，China and College of Aerospace and Material Technology，National University of Defence Technology，Changsha 410073，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究进气道喉道非均匀流场对隔离段流动特性的影响，设计了能模拟隔离段入射激波和非对称附面层的直连试验装置，并进行了马赫数 3.0，3.4和 3.8的吹风试验，完成了壁面静压、纹影和 NPLS测量，获得了有效的试验数据。结果显示，唇口角对隔离段直连台的起动和耐反压能力影响非常大，随着唇口角度的增加，隔离段的极限反压降低，降低幅度达到 22%～32%。与均匀来流相比，激波串很难稳在隔离段入口附近，造成激波串极易被推出隔离段。激波串形态受隔离段入射激波和肩部附近附面层状态的影响较大。 NPLS测量系统观察到隔离段内部流场精细结构，如下壁面附面层的转捩现象、激波串的马赫盘、分离和滑移线等。

关键词: 隔离段；激波串；非均匀来流

Abstract: In order to investigate the effects of nonuniform flow at inlet throat on the flow characteristics of isolators，a direct connected experimental facility was designed to simulate the lip shock wave and asymmetricboundary layer at the isolator entrance. The experiment with nonuniform flows at the isolator entrance was con.ducted in a wind tunnel at Mach 3.0，3.4 and 3.8，respectively. Pressure distribution at wall，schlieren photograph and Nano-tracer Planar Laser Scattering(NPLS)were measured in the experiments. The results indicate that lipangle has significant effects on the starting and anti-pressure capability of isolator. With the increase of lip angle， the maximum back pressure of the isolator decreases and the range is between 22% and 32%. Shock train in theisolator with a nonuniform entrance flow is relatively more unstable and easily being pushed out of the isolatorcompared with that of a uniform entrance flow. The lip shock wave and asymmetric boundary layer have great in.fluence on the shape of shock train. Results show that flow structures such as transition phenomenon on the lowerwall，mach disk，separation flow and slip lines could be revealed distinctly by NPLS.

Key words: Isolator；Shock train；Asymmetric flow

曹学斌,朱守梅,满延进,易仕和,陈植. 考虑进气道喉道非均匀流场影响的隔离段直连试验[J]. 推进技术, 2015, 36(4): 547-555.

CAO Xue-bin¹,ZHU Shou-mei¹,MAN Yan-jin¹,YI Shi-he²,CHEN Zhi². DirectionConnectTestonIsolatorConsideringEffectsof NonuniformFlowatInletThroat[J]. Journal of Propulsion Technology, 2015, 36(4): 547-555.

参考文献

[1] 金志光,张堃元,刘媛.马赫数 4～7的高超侧压式进气道气动设计与性能[ J].航空动力学报, 2011, 26(6):1201-1208.
[2] 肖雅彬,岳连捷,龚鹏,等 .三面压缩式高超声速进气道流动结构研究[ J].实验流体力学, 2008,22(2): 64-67.
[3] 南向军,张堃元,金志光,等 .矩形转圆形高超声速内收缩进气道数值及试验研究[ J].航空学报, 2011, 32(6): 988-996.
[4] 朱呈祥,黄国平,尤延铖,等 .内乘波式进气道与典型侧压式进气道的性能对比[ J].推进技术, 2011,32(2):151-158.(ZHU Cheng-xiang,HUANG Guo-ping, YOU Yan-cheng,et al.Performance Comparison Be.tween Internal Waverider Inlet and Typical SidewallCompression Inlet[J].Journal of Propulsion Technolo.gy,2011,32(2):151-158)
[5] Saied Emami,Carl A Trexler,Aaron H Auslender,et al.Experimental Investigation of Inlet-Combustion Iso.lators for a Dual-Mode Scramjet at a Mach Number of 4[R].NASA TP-3502,1995.
[6] 张堃元,王成鹏,杨建军,等 .带高超进气道的隔离段流动特性[ J].推进技术, 2002,23(4): 311-314.(ZHANG Kun-yuan,WANG Cheng-peng,YANG Ji.an-jun,et al.Investigation of Flow in Isolator of Hyper.sonic Inlet[J].Journal of Propulsion Technology, 2002,23(4):311-314.)
[7] 王成鹏,张堃元,杨建军 .带进气道的隔离段流场实验研究与数值模拟[ J].推进技术, 2004,25(1):27-31.(WANG Cheng-peng,ZHANG Kun-yuan,Yang Ji.an-jun.Experimental and Numerical Investigation ofIsolator Combined with Hypersonic Inlet[J].Journal of Propulsion Technology,2004,25(1):27-31)
[8] Hui-jun Tan,Shu Sun.Preliminary Study of ShockTrain in a Curved Variable-Section Diffuser[J].Jour.nal of Propulsion and Power,2008,24(2):245-252.
[9] 王成鹏,张堃元,金志光,等 .非均匀超声来流矩形隔离段内流场实验[ J].推进技术, 2004,25(4): 349-353.(WANG Cheng-peng,ZHANG Kun-yuan, JIN Zhi-guang,et al.Experimental Investigation on In.ternal Flow in Rctangular Isolator under Non-Uniform Supersonic Flow[J].Journal of Propulsion Technology, 2004,25(4):349-353.)
[10] 王成鹏,张堃元 .隔离段进口非对称来流对激波串结构的影响[ J].南京航空航天大学学报(英文版), 2006,23(1):1-7.
[11] 王成鹏 .非对称来流条件下超燃冲压发动机隔离段气动特性研究[ D].南京 :南京航空航天大学, 2005.
[12] ZHAO YuXin,YI ShiHe,TIAN LiFeng et al.Superson.ic Flow Imaging Via Nanoparticles[J].Science in Chi.na: E,2009,52(12):3640-3648.
[13] 赵玉新,易仕和,田立丰,等 .基于纳米粒子的超声速流动成像[ J].中国科学 E辑:技术科学, 2009, 39(12): 1911~1918.
[14] 易仕和,何霖,田立丰,等 .纳米示踪平面激光散射技术在激波复杂流场测量中的应用[ J].力学进展, 2012,42(2):197~205.
[15] Zhi Chen,Yi Shihe,Zhu Yangzhu,et.Investigation onFlows in a Supersonic Isolator with an Adjustable CowlConvergence Angle[J].Experimental Thermal and Flu.id Science,2014,52(2014):182~190.
[16] Waltrup P J,Billig F S.Structure of Shock Waves in Cy.lindrical Ducts[J].AIAA Journal,1973,11(10): 1404-1408.
[17] Carroll B F,Dutton J C.Characteristics of MultipleShock Wave/Turbulent Boundary Layer Interactions inRectangular Ducts[J].Journal of Propulsion Power, 1990,6(2):186-193.
[18] Carroll B F,Dutton J C.Turbulence Phenomena in a Multiple Normal Shock Wave/Turbulent Boundary-Lay.er Interaction[J].AIAA Journal,1992,30(1):43-48.
[19] 曹学斌,张堃元,王成鹏 .非对称来流下隔离段动态压力特性[ J].推进技术, 2009,30(1):57-62.(CAO Xue-bin,ZHANG Kun-yuan,WANG Cheng-peng.Characteristics of Wall Pressure Fluctuations in Straight Isolator with Asymmetric Incoming Flow[J],aJournal of Propulsion Technology,2009,30(1):57-62.)(编辑:梅瑛)* 收稿日期:2014-02-23；修订日期:2014-05-13。作者简介:曹学斌( 1984—),男,博士,工程师,研究领域为内流气体动力学。 E-mail:xuebincao@126.com