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摘要本文提出一种冲压发动机旋流模拟器的设计方法，以旋流数0.5为基准确定了旋流模拟器的几何参数。针对16种来流工况设计了限流喉道，为减小流动损失设计了整流锥，组合限流喉道、旋流器和整流锥，建立计算模型，并对其进行数值仿真。分别研究16种来流工况下气体在计算模型中的流动特性，得到了气体在计算模型出口的流动参数，发现这些参数随气体质量流率的增大而增大。本文根据仿真结果计算出总压恢复系数和旋流数，发现限流喉道的总压损失较大且随模拟来流马赫数增大而增大，旋流器的总压损失及其变化范围均较小，旋流数与气流状态无关，只取决于旋流器本身的几何参数。60225
关键词 冲压发动机 旋流模拟器 旋流 设计 数值仿真
毕业设计说明书（毕业论文）外文摘要
Title The Design and Numerical Simulation of the Swirler for Ramjets
Abstract
A method was devised for the design of the swirler for ramjets. The geo- metrical parameters of the swirler were determined on the basis of swirl number assigned 0.5. Flux-limiting throats were designed for 16 different airflow conditions. In order to decrease the flux loss, fairing cones were devised. A calculation model were composed with a Flux-limiting throat, a swirler and a fairing cone. The calculation models was numerically si- mulated to study the flow properties with 16 airflow conditions.A series of flow parameters in the exit of calculation model were obtained and it can be found that these parameters increased with the increase of mass flow rate. Based on the results of numerical simulation,the total pressure recovery coefficients and swirl numbers were caculated. The total pressure loss of the airflow in Flux-limiting throats were obvious and increased with the increase of mach number. The total pressure loss of the airflow in swirlers were slight as well as their variation range. The swirl numbers were independent of flowing situation，and they were determined by the swirls’geometrical parameters.
Keywords ramjet swirler swirl design numerical simulation
目 录
1 绪论 1
1.1 概述 1
1.2 研究的背景及意义 3
1.4 本文的主要工作 5
2 冲压发动机旋流模拟器的设计 6
2.1 旋流器的设计与计算 6
2.2 限流喉道设计及其出口气流状态参数计算 10
2.3 整流锥设计 15
2.4 本章小结 16
3 冲压发动机旋流模拟器的仿真 16
3.1 基本假设和控制方程 17
3.2 湍流模型 18
3.3 计算模型及网格划分 19
3.4 边界条件 21
3.5 求解方法和初场值的给定 22
3.6 计算流程 23
3.7 本章小结 23
4 数值仿真结果与分析 24
4.1 流场计算云图