内转式进气道自起动性能研究
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摘要
为了研究内转式进气道的自起动性能以及下壁面泄流对自起动的影响规律,开展了数值计算和风洞实验,数值计算采用准定常的方法,风洞实验通过阴影录像以及下壁面丝线显示相结合的方法确定进气道的起动状态。结果表明Ma5、攻角0°时进气道不能自起动,下壁面存在大范围的三维流动分离,流动损失严重。为了提高进气道的自起动能力,在下壁面距前缘400mm位置开孔泄流,开孔区域约100mm×40mm,开孔率0.2,实验模型孔径3mm;研究表明,泄流后进气道顺利自起动,总压恢复系数提高了0.25,泄流量损失仅为捕获流量的1%。进一步数值研究表明,泄流构型在攻角0°时的自起动马赫数在4.3～4.4,泄流极大地拓宽了进气道的工作范围。
Aiming at a detailed investigation on the self-starting characteristics of an inward turning inlet,and the influence of bleeding at the down-wall,studies using both numerical simulations and wind tunnel experiments were carried out.The numerical simulations are conducted using quasi-steady methods.In the experiments,the surface tuft flow visualization technique is used to detect the starting state of the inlet,combined with shadowgraph images.Both numerical and experimental results show that the inlet can not self-start at Ma5,attack angle 0°,and there are large-scale flow separations at the down-wall,leading to severe flow loss.In order to enhance the self-starting capability of the inlet,a porous region composed of a large amount of bleeding holes whose diameters are 3 mm is used at 400 mm downstream of the leading edge of the down-wall.The area of the region is 100 mm×40 mm and the bleeding porosity is 0.2.Results show that with the help of the bleeding holes,the inlet self-starts successfully and the total pressure recovery coefficient increases by 0.25,the flux loss due to the bleeding holes is only 1% of the captured mass flow rate.Further numerical simulations show that the self-starting Mach number of the inlet with bleeding holes is between Ma4.3 and Ma4.4 at attack angle 0°,indicating that appropriate bleeding is able to broaden the working range of the inlet.
Aiming at a detailed investigation on the self-starting characteristics of an inward turning inlet,and the influence of bleeding at the down-wall,studies using both numerical simulations and wind tunnel experiments were carried out.The numerical simulations are conducted using quasi-steady methods.In the experiments,the surface tuft flow visualization technique is used to detect the starting state of the inlet,combined with shadowgraph images.Both numerical and experimental results show that the inlet can not self-start at Ma5,attack angle 0°,and there are large-scale flow separations at the down-wall,leading to severe flow loss.In order to enhance the self-starting capability of the inlet,a porous region composed of a large amount of bleeding holes whose diameters are 3 mm is used at 400 mm downstream of the leading edge of the down-wall.The area of the region is 100 mm×40 mm and the bleeding porosity is 0.2.Results show that with the help of the bleeding holes,the inlet self-starts successfully and the total pressure recovery coefficient increases by 0.25,the flux loss due to the bleeding holes is only 1% of the captured mass flow rate.Further numerical simulations show that the self-starting Mach number of the inlet with bleeding holes is between Ma4.3 and Ma4.4 at attack angle 0°,indicating that appropriate bleeding is able to broaden the working range of the inlet.
引文
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[19]梁德旺,钱华俊.抽吸孔板的气动实验及附面层抽吸数值模拟[J].航空学报,2002,23(6):512-516.
[20]Slater J W.Improvements in Modeling 90-Degree Bleed Holes for Supersonic Inlets[J].Journal of Propulsion and Power,2012,28(4):774-781.
[21]杨大伟,余安远.泄流对高超声速内转式进气道自起动性能影响研究[C].哈尔滨:第八届全国高超声速科技学术会议,2015.
[22]Donde P,Marathe A G,Sudhakar K.Starting in Hypersonic Intakes[R].AIAA 2006-4510
[23]YU Anyuan,YANG Dawei,WU Jie,et al.The Numerical Simulation Techniques Research and Preliminary Experimental Validation of the Start Characteristics for a Two-Dimensional Hypersonic Inlet[C].Krakow:6th European Conference for Aeronautics and Space Sciences(EUCASS),2015.
[2]You Y.An Overview of the Advantages and Concerns of Hypersonic Inward Turning Inlets[R].AIAA 2011-2269.
[3]田方超.内转式高超声速进气道的不起动问题研究[D].南京:南京航空航天大学,2013.
[4]Steven Walker,Ming Tang.Falcon HTV-3X-A Reusable Hypersonic Test Bed[R].AIAA 2008-2544.
[5]Adam Siebenhaar,Thomas J Bogar.Integration and Vehicle Performance Assessment of the Aerojet“TriJet”Combined-Cycle Engine[R].AIAA 2009-7420.
[6]Meerts C,Steelant J.Air Intake Design for the Acceleration Propulsion Unit of the LAPCAT-MR2 Hypersonic Aircraft[C].Munich:5th European Conference for Aeronautics and Space Sciences,2013.
[7]Michael K Smart,Carl A Trexler.Mach 4 Performance of a Fixed-Geometry Hypersonic Inlet with Rectangularto-Elliptical Shape Transition[R].AIAA 2003-0012.
[8]Billig F S,Baurle R A.Design and Analysis of Streamline Traced Hypersonic Inlets[R].AIAA 99-4974.
[9]尤延铖,梁德旺,黄国平.一种新型内乘波式进气道初步研究[J].推进技术,2006,27(3):252-256.(YOU Yan-cheng,LIANG De-wang,HUANG Guoping.Investigation of Internal Waverider-Derived Hypersonic Inlet[J].Journal of Propulsion Technology,2006,27(3):252-256.)
[10]尤延铖,梁德旺.内乘波式进气道内收缩基本流场研究[J].空气动力学学报,2008,26(2):203-207.
[11]卫锋,贺旭照,贺元元,等.三维内转式进气道对双旁进气道飞行器力矩特性的影响分析[J].推进技术,2014,35(11):1441-1447.(WEI Feng,HE Xuzhao,HE Yuan-yuan,et al.Effects Analysis of 3D Inward Turning Inlet on Moment Characteristics of Vehicle with Inlets Decorated in Both Sides[J].Journal of Propulsion Technology,2014,35(11):1441-1447.)
[12]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实验研究[J].航空学报,2011,32(6):988-996.
[13]Jacobsen L S,Tam C J,Robert B F.Starting and Operation of a Streamline-Traced BusemannInlet at Mach 4[R].AIAA 2006-4508.
[14]Stephen E J,Hoenisch S R,Waddel M L,et al.HIFiRE 6 Unstart Conditions at Off-Design Mach Numbers[R].AIAA 2015-0109.
[15]黄舶,李祝飞,杨基明,等.激波风洞内超燃冲压发动机三面压缩进气道流场实验观测[J].实验力学,2012,27(1):23-29.
[16]黄舶.高超声速内外流动激波/边界层相互作用的实验与数值研究[D].合肥:中国科学技术大学.2013.
[17]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.
[18]杨大伟,余安远.泄流对高超声速内转式进气道自起动性能影响研究[C].上海:中国力学大会,2015.
[19]梁德旺,钱华俊.抽吸孔板的气动实验及附面层抽吸数值模拟[J].航空学报,2002,23(6):512-516.
[20]Slater J W.Improvements in Modeling 90-Degree Bleed Holes for Supersonic Inlets[J].Journal of Propulsion and Power,2012,28(4):774-781.
[21]杨大伟,余安远.泄流对高超声速内转式进气道自起动性能影响研究[C].哈尔滨:第八届全国高超声速科技学术会议,2015.
[22]Donde P,Marathe A G,Sudhakar K.Starting in Hypersonic Intakes[R].AIAA 2006-4510
[23]YU Anyuan,YANG Dawei,WU Jie,et al.The Numerical Simulation Techniques Research and Preliminary Experimental Validation of the Start Characteristics for a Two-Dimensional Hypersonic Inlet[C].Krakow:6th European Conference for Aeronautics and Space Sciences(EUCASS),2015.