混合层（尾迹）/边界层组合流动机理研究

项目名称： 混合层（尾迹）/边界层组合流动机理研究

项目编号： No.51476152

项目类型： 面上项目

立项/批准年度： 2015

项目学科： 能源与动力工程

项目作者： 刘凤君

作者单位： 中国航天科工飞航技术研究院

项目金额： 84万元

中文摘要： 混合层（尾迹）与边界层之间相互干扰流动常见于航空飞行器和航空发动机燃烧室，深入认识其流动机理在控制流动方面发挥重要作用。对无化学反应或有化学反应的混合层/边界层合流的流动，进行流动不稳定性研究，辨识受边界层影响的混合层（尾迹）不稳定扰动波的模式及受混合层（尾迹）影响的边界层不稳定扰动波的模式，揭示混合层（尾迹）和边界层中最不稳定波的失稳机制，研究混合层（尾迹）增长规律。在流动不稳定性研究基础上，建立初始流动模型，采用大涡模拟方法数值模拟混合层（尾迹）/边界层合流的反应流动，刻画这种流动的非线性特征，研究在下游流场的流动演化过程。基于组合流动机理的研究结果，进行流动控制研究，从主动控制和被动控制的角度，提出增强流动掺混的基础方法。

中文关键词： 工程热物理；数值模拟；边界层；计算流体动力学

英文摘要： The confluent mixing layer(wake)/boundary layer flow is often observed in aircrafts,and aeroengine combustors. Deeply understanding the confluent flow meachanism plays an importance role in controlling the flow development. The linear stability theory(LST) will be used to study the confluent mixing layer(wake)/boundary layer flow with or without chemical reactions.The unstable wave modes associated with both the mixing layer(wake) and boundary layer due to their interactions will be the identified. The unstability mechanism of the most unstable waves will be revealed. The regular pattern of the mixing layer (wake) growth will be studied. Based on the LST research results, an initial flow model will be established. The large eddy simulation will be employed to numerically simulate the confluent mixing layer/boundary layer reacting flow, mimic its non-linear characteristics, and study the flow evolution process downstream.The flow control study will be conducted according to the results for the confluent flow mechanism. The fundamental approaches to strengthen the flow mixing will be given in view of the active and paasive ways.

英文关键词： Engineering Thermodynamics;Numerical Simulation;Boundary Layer;CFD