扩压器入口面积比对自由旋涡气动窗口性能的影响

 针对采用主动式扩压器的自由旋涡气动窗口,实验考察了扩压器入口面积比对扩压器压力恢复性能及自由旋涡气动窗口密封性能的影响。结果表明：入口面积比是影响扩压器压力恢复性能的重要因素;通过优化扩压器入口面积比,可以提高气动窗口密封压比和稳定性。主动式扩压器比传统扩压器具有更小的最佳入口面积比,使气动窗口射流更接近于理想自由旋涡射流;主动式扩压器最佳入口面积比约为2.03。在最佳入口面积比情况下,扩压器内端壁吹气临界驻室压力最低,外端壁吹气压力对密封压力基本没有影响。     

大密封压比超音速自由旋气动窗口设计与试验研究

 介绍了横向超音速自由旋气动窗口设计方法,分析了单级气动窗口难以实现大密封压比的原因。针对气动窗口扩压器入口气动参数分布特点,提出了一种扩压器带端壁吹气的气动窗口设计方案并进行了试验验证,气动窗口密封压比达到了85。结果表明：扩压器入口端壁吹气是一种有效提高气动窗口密封压比的技术措施,内端壁吹气对密封压比影响较大,外端壁吹气对密封压比影响较小。     

用剪切干涉法测气动窗口流场对光束质量的影响

 利用横向剪切干涉仪对测量环境要求不高的优点,提出用横向剪切干涉仪测量气动窗口流场对光束质量的影响;给出测量原理,解决了干涉条纹难以判读的难点。并对稳定工作状态下自由旋涡气动窗口流场对光束质量的影响进行实验研究。以斯特列尔比为评价标准,测量给出自由旋涡气动窗口在稳定工作状态下对光束质量的影响程度。结果表明,当自由旋涡气动窗口工作在理论设计条件下时,对光束质量的影响比较小,能较好满足任务需要。     

自由旋涡气动窗口自适应光学波前校正初步研究

自由旋涡气动窗口能有效地替代高能激光器传统晶体输出镜 ,起到密封激光器低腔压的作用。利用现有的 37单元室内自适应光学系统 ,对自由旋涡气动窗口的输出激光波前畸变进行自适应光学波前校正。给出了自适应光学系统对气动窗口畸变波前的校正原理 ,采用直接斜率法在设计状态下对畸变波前进行了校正实验。结果表明 ,该自适应光学系统能够较好地校正工作在设计状态下的自由旋涡气动窗口对输出激光所引起的波前畸变     

自由旋涡气动窗口自适应光学波前校正初步研究

 自由旋涡气动窗口能有效地替代高能激光器传统晶体输出镜，起到密封激光器低腔压的作用。利用现有的37单元室内自适应光学系统，对自由旋涡气动窗口的输出激光波前畸变进行自适应光学波前校正。给出了自适应光学系统对气动窗口畸变波前的校正原理，采用直接斜率法在设计状态下对畸变波前进行了校正实验。结果表明，该自适应光学系统能够较好地校正工作在设计状态下的自由旋涡气动窗口对输出激光所引起的波前畸变。     

吹气抑制气体热效应时管道结构对光传输的影响

 采用吹气抑制气体热效应对光传输的影响时，管道结构会对内通道流场分布产生作用从而影响光传输质量。对比研究了沿几何尺寸相同、光路总长相等的U形和Z形管道轴向吹气的情形。仿真过程中，联合求解标量衍射方程和N-S方程,计算管道对吹气流场的影响以及流场对光束的影响，以远场光斑的峰值功率密度点、能量分布重心点位置的偏移以及Strehl比和b值的变化反映光束质量。结果表明:不吹气时，管道结构对流场的影响远小于气体吸热对流场的影响；吹气时，管道内气体流速较大，管道结构对流场分布的影响比较明显；吹气时，U形管道对光束的影响比Z形管道对光束的影响要小。     

引射式气动窗口的光束质量研究

 实验研究了引射式气动窗口喷流引射对输出光束质量的影响,给出了不同引射喷管喉道尺寸下,不同引射喷流滞止压力时的气动窗口光学特性参数,其中包括:Strehl强度比,波像差最大值,波阵面形状,均方根值以及调制传递函数。实验表明,除引射喷管喉道尺寸dH=2.5mm,引射喷流滞止压力为0.5MPa工况外,其它工况时喷流引射对输出光束质量影响很小。因此引射式气动窗口可以保证输出高质量的光束。     

用远场法研究自由旋气动窗口的光学特性

 采用He-Ne激光,对穿过自由旋气动窗口的远场聚焦光斑进行图象采集和数据处理,研究本气动窗口对透过其输出通道的激光束所带来的偏转和随机抖动现象,计算分析气动窗口对激光束发散特性的影响,定义和实验研究气动窗口的光束质量β因子。同时,分析讨论气动窗口对激光束远场聚焦光斑光强分布的影响,并提出气动窗口光束质量和气动窗口设计的进一步研究思路。     

用哈特曼法研究自由旋涡气动窗口光束质量

 利用37单元哈特曼波前传感器实验研究不同工作条件下不同时刻自由旋涡气动窗口对输出激光波前的影响。将高速CCD所采集的畸变激光波前传送给高速波前处理机，采用模式法对其进行波前重构，进而计算给出畸变波前的波像差峰谷值、波像差均方根和斯特列尔比值等相关光学参数随气动窗口工作条件不同的变化曲线。结果表明，自由旋涡气动窗口对输出激光波前的影响主要是光束偏转和离焦，特别是气动窗口工作在设计状态时，其余低阶及高阶像差都比较小，能够满足实际需要。哈特曼波前传感器能很好地用于自由旋涡气动窗口对激光波前影响的二维动态测量，并能给出波前畸变的各项Zernike多项式的模式系数得到畸变波前，直接为气动窗口与强激光发射系统的对接和波前校正提供数据。     

端壁凹槽控制扩压叶栅角区分离的数值研究

为揭示端壁凹槽控制高速扩压叶栅角区分离、降低叶栅气动损失的物理机制,采用数值方法研究了高速扩压叶栅NACA65-K48附加具有不同轴向位置和横向长度的端壁凹槽时叶栅的流场结构和气动特性.结果 表明:叶栅出口总压损失系数最大降低8.08％,静压升约提高0.67％.近端壁气流在凹槽内部诱导出复杂旋涡结构,该旋涡结构反过来为...     

Studies on the Aero-optical Phenomena of Free-vortex Aerodynamic Window′s Jet

The concept of the free-vortex aerodynamic windows(FADW) is one of the best effective methods taking the place of the conventional beam output crystal windows of high power laser. An experimental model of the supersonic free-vortex aerodynamic window has been designed and made in our latest study. This paper studies the aero-optical phenomena of the FADW′s supersonic jet to study the laser optical quality degradation caused by the free-vortex jet, and to find out the relation of output laser beam quality through the FADW to the structure of the FADW′s supersonic jet. First it studies the beam quality using the methods of far-field beam profile measurement and lateral shearing interferometry, and then it uses the principle of matrix-optics interpreting the large-scale phase distortion in detail. At last the structure of FADW′s jet has been studied by means of shadowgraphy.     

Studies on the Aero-optical Phenomena of Free-vortex Aerodynamic Window′s Jet

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PIV studies of large scale structures in the near field of small aspect ratio elliptic Jets

The near flow field of small aspect ratio elliptic turbulent free jets (issuing from nozzle and orifice) was experimentally studied using a 2D PIV Two point velocity correla tions in these jets revealed the extent and orientation of the large scale structures in th e major and minor planes. The spatial filtering of the instantaneous velocity field using Gaussian convolution kernel shows that while a single large vortex ring circumscribing the jet seems to be present at the exit of nozzle, the orifice jet exhibited a number of smaller vortex ring pairs close to jet exit. The smaller length scale observed in the case of the orifice jet is rep resentative of the smaller azimuthal vor tex rings that generate axial vortex field as they are convected. This results in the axis-switching in th e case of orifice jet and may have a mechanism differ ent from the self induction process as observed in the case of contoured nozzle jet flow.     

Near-field acoustic characteristics of screech jet exhausted from a nozzle with a hard reflecting plate

The standing wave in the near field of the screech jet exhausted from a nozzle with a hard plate works on the jet flow as the forcing wave by the location of a reflecting plate, and then jet flow is considered to be changed. Moreover, the reflector location from the nozzle changes the sound pressure contours of the near field. Intensity maps of the screech tone which indicate the propagation to the jet axial direction or the radial direction of the jet by the presence of the reflector plate have not been explored. In the present paper, acoustic characteristics in the near field of the screech tone with the reflecting plate are studied using an optical wave microphone, which can measure the sound propagating for both vertical and horizontal directions to the jet axis. As a result, the standing wave in the near field of the screech jet with the reflector has two types: One is the standing wave between the hydrodynamic pressure fluctuation propagating jet downstream and the sound pressure propagating upstream, and the other is the standing wave by the difference between the wavelength of the sound wave and the wavelength at the place close to the jet.     

Numerical flow visualization of a Single Expansion Ramp Nozzle with hypersonic external flow

Numerical simulation of scramjet asymmetric nozzle flow is carried out to visualize and investigate the effects of interaction between engine exhaust and hypersonic external flow. The Single Expansion Ramp Nozzle (SERN) configuration studied here consists of flat ramp and a cowl with different combinations of ramp angle and cowl geometry. UsingPARAS 3D, simulations are performed for a free stream Mach number of 6.5 that constitutes the external flow around the vehicle. Appropriate specific heats ratio has been simulated for the jet and free stream flow. External shock wave due to jet plume interaction with free stream flow, the internal barrel shock wave and the shear layer emanating from the cowl trailing edge and sidewalls are well captured. Wall static pressure distribution on the nozzle ramp for different nozzle expansion angles has been computed for both with and without side fence. Axial thrust and normal force have been evaluated by integrating the wall static pressure. Effect of cowl length variation and side fence on the SERN performance has also been studied and found to be quite significant. Based on this study, an optimum ramp angle at which the SERN generates maximum axial thrust is obtained. SERN angle of 20° was found to be optimum when the flight axis coincides with nozzle axis.     

Flow visualization of vortex structure in a pulsed rectangular jet

Pulsating jet is visualized using hydrogen bubble method to clarify the vortex nature in the near field of the jet. This study focused on the development in space and time of vortex structures evolution in low aspect-ratio rectangular jet with pulsation. Pulsation means large-amplitude, low-frequency excitation which is expected to increase the mixing and spreading of the jet and to accelerate its transition from a rectangular form to an axisymmetric form. It was deemed appropriate to investigate whether jet characteristics of a pulsating, submerged jet flow can be altered by including pulsations. The difference of the vortex deformation process is discussed in relation to pulsating conditions. Consequently, the pulsation leads to the formation of vortices at regular intervals, which are larger than those occurring in a steady jet. The results show that the streamwise interaction, between leading vortex and trailing vortex rolled up at nozzle lips, strengthens with increasing pulsating frequency. The spanwise drift of the vortex becomes strongly apparent at large amplitude and high frequency conditions. The drifting start position does not change regardless of pulsating condition. The convection velocity of vortex increases at lower frequency and larger amplitude.     

COIL亚声速段横向喷流混合流场数值分析

 COIL是一个气体动力学、化学反应动力学以及光学相互耦合的复杂过程。作为高总压COIL系统研究的第一步,利用三维CFD技术对传统的COIL亚声速段横向射流混合过程进行了数值分析,讨论了包括压力梯度驱动项的分子扩散机制,得到了横向射流的较精细的结构,如马蹄形射流界面、逆旋涡对以及射流剪切层。结果表明,压力梯度驱动项对重、轻组分的扩散作用相反,重组分沿压力梯度正向扩散,轻组分逆压力梯度方向扩散。在射流穿透不足的情况下,仍然在喷管出口得到了约为0.01 cm^-1的小信号增益系数。