摘要涡轮基组合循环(TBCC)发动机是未来高超声速飞行器最适合的动力系统之一。本文提出一种内并联双通道的涡轮基组合循环进气道设计方案，进行了初步的气动设计研究，主要包括1.适应高马赫数（Ma2.5-6）的双通道二元可调进气道初步设计；2.M2.5-M6双通道二元可调进气道数值模拟，其中使用fluent软件对模型进行了流场数值模拟，研究了转接点时高速通道的启动问题和转换过程中两个通道的相互干扰问题；3.通过数值模拟获得该进气道的流场特性并验证进气道性能。69434

毕业论文关键词   涡轮基组合循环(TBCC)  内并联双通道  高马赫数   数值模拟  进气道

毕业设计说明书外文摘要

Title    Numerical simulation of TBCC variable geometry   two-dimensional inlet                            

Abstract

Turbine based combined cycle (TBCC) engine is one of the most suitable power system for hypersonic aircraft in the future.This paper present a parallel dual channel of turbine based combined cycle inlet design and of preliminary aerodynamic design and research， including 1. Preliminary design of dual channel variable geometry two-dimensional inlet adapted to high Mach number (Ma2.5-6) ; 2.numerical simulation of M2.5-M6 dual channel variable geometry two-dimensional inlet， including the numerical simulation of the flow field of the model used by FLUENT software and studying on the problem of mutual interference of two channels and starting of conversion of the high-speed channel at transfer point ; 3. Through the numerical simulation for the flow field characteristics of inlet and verify the performance of the inlet.

Keywords  TBCC  over/under dual channel  high Mach number   numerical simulation   inlet

目   次

1 引言 1

1.1 研究背景 1

1.2 TBCC进气道国内外研究现状 2

1.2.1外国TBCC进气道发展状况 2

1.2.2 TBCC进气道国内发展状况 3

1.3 本课题的研究内容 5

2 进气道的设计 6

2.1 外压段的计算 9

2.2 绘图软件UG的准备 12

2.3 内压段的计算 12

3 数值模拟仿真 13

3.1 仿真软件的准备及介绍 13

3.1.1 网格的绘制ICEM 13

3.1.2 数据的计算仿真FLUENT 14

3.2 计算结果 14

3.2.1 网格绘制 14

3.2.2 高速通道流场特性及起动特性 15

3.2.3 模态转换点流场特性及性能 17

结  论 25

致  谢 26

参 考 文 献 27

1 引言