超声速气流中液体横向射流的非定常特性与振荡边界模型

发布时间：2019-02-13 12:29

【摘要】：针对液体圆柱射流垂直喷入超声速横向气流中的非定常分布特性开展实验研究,并建立穿透深度方向上的射流振荡分布模型.利用脉冲激光背景成像方法 "冻结"拍摄马赫2.1(Ma=2.1)气流中煤油射流/喷雾瞬态图像,结合最大类间方差法(Otsu)和Canny算法提取瞬态图像特征,基于统计方法并引入间歇因子(γ)定量描述射流振荡分布特性;通过研究多参数协同作用下的射流振荡分布规律,提出振荡分布数学模型,研究的参数变量包括超声速来流总压(642—1010 k Pa)、液体喷注压降(0.36—4.61 MPa)、液体喷嘴流道直径(0.48 mm/1.0 mm/1.25 mm/1.52 mm)、距离喷嘴的流向距离(10—125 mm)以及液气动量通量比(0.11—7.49).研究中利用射流振荡分布模型成功预测出水射流在Ma=2.1气流中的的振荡分布,预测分布与实验结果符合良好.
[Abstract]:An experimental study on the unsteady distribution of liquid cylindrical jets vertically injected into supersonic transverse flow is carried out, and a model for the distribution of jet oscillations in the direction of penetration depth is established. The pulse laser background imaging method "freezing" was used to capture the kerosene jet / spray transient images in Mach 2.1 (Ma=2.1) airflow, and the (Otsu) and Canny algorithms were used to extract the transient image features. Based on the statistical method, a batch factor (纬) is introduced to quantitatively describe the distribution of jet oscillation. By studying the distribution of jet oscillation under the multi-parameter synergistic action, a mathematical model of oscillation distribution is proposed. The parameter variables studied include the total pressure of supersonic incoming flow (642-1010 k Pa),) and the pressure drop of liquid injection (0.36-4.61 MPa),). The flow direction distance (10-125 mm) and the flux-flux ratio (0.11-7.49) of the liquid nozzle flow channel (0.48 mm/1.0 mm/1.25 mm/1.52 mm),). In the study, the oscillatory distribution of water jet in Ma=2.1 flow was successfully predicted by using the model of jet oscillation distribution, and the predicted distribution was in good agreement with the experimental results.
【作者单位】：国防科学技术大学高超声速冲压发动机技术重点实验室;
【基金】：国家自然科学基金(批准号:11472303) 新世纪优秀人才支持计划(批准号:NCET-13-0156)资助的课题~~
【分类号】：O358

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