高速复杂流动PIV技术研究实践与挑战

发布时间：2018-05-31 12:58

本文选题：高速复杂流场 + PIV技术　；参考：《实验流体力学》2016年01期

【摘要】：粒子图像测速技术目前已经发展成为实验流体力学领域应用最广泛的非接触激光测试方法之一,为认知复杂流动机理提供直观的流场信息。本文基于超声速流场PIV技术研究实践,针对示踪粒子布撒器设计、粒子松弛特性模型构建、激波流场测试分析、超声速平板湍流边界层结构分析等方面具体问题的研究和认识,从理论、定量化的角度深入分析了应用于超声速流场PIV技术现阶段依然存在的问题。从应用于超声速流场PIV技术的原理出发,针对高速复杂流场的PIV测试现状,总结了应用于超声速流场PIV技术发展过程中的光学部件、示踪粒子及布撒系统所遇到的一系列挑战,以及国内外利用PIV技术在高速复杂流场研究中所取得的成就,针对PIV技术能否适用于高超声速流场的测量做了系统化地探索。并根据实践经验提出了应用于超声速流场PIV技术未来的发展方向:通用的精确的PIV方法不存在,必须从具体研究的流动机理角度改造相应的PIV测试手段。
[Abstract]:Particle image velocimetry has been developed into one of the most widely used non-contact laser measurement methods in the field of experimental fluid dynamics, which provides intuitive flow field information for cognition of complex flow mechanism. Based on the research practice of supersonic flow field PIV technology, this paper focuses on the design of tracer particle dispenser, the construction of particle relaxation characteristic model, the measurement and analysis of shock flow field, and the analysis of supersonic plate turbulent boundary layer structure. In this paper, the problems existing in supersonic flow field PIV technology are analyzed theoretically and quantitatively. Based on the principle of supersonic flow field PIV technology and the current situation of PIV measurement for high-speed complex flow field, this paper summarizes a series of challenges in the development of supersonic flow field PIV technology, such as optical components, tracer particles and distribution system. As well as the achievement of using PIV technology in the research of high speed and complex flow field at home and abroad, this paper systematically explores whether PIV technology can be applied to the measurement of hypersonic flow field. According to the practical experience, the future development direction of the supersonic flow field PIV technology is put forward: the general and accurate PIV method does not exist, and the corresponding PIV testing means must be reformed from the point of view of the specific flow mechanism.
【作者单位】：上海交通大学航空航天学院;中国空气动力研究与发展中心;
【基金】：国家自然科学基金项目(91441205;91330203)
【分类号】：O35

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