内转式进气道自起动性能研究  

Study on Self-Starting Characteristics of an Inward Turning Inlet

作　　者：杨大伟[1,2] 余安远 韩亦宇[1] 卫锋 丁国昊[1] 曲俐鹏 YANG Da-wei;YU An-yuan;HAN Yi-yu;WEI Feng;DING Guo-hao;QU Li-peng(Science and Technology on Scramjet Laboratory,Hypervelocity Aerodynamics Institute of CARDC, Mianyang 621000,China;School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]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,四川绵阳621000 [2]西北工业大学航空学院,陕西西安710072

出　　处：《推进技术》2019年第1期76-83,共8页Journal of Propulsion Technology

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.

关 键 词：内转式进气道 起动 数值模拟 风洞实验 泄流 

分 类 号：V411.7[航空宇航科学与技术—航空宇航推进理论与工程]