TBCC发动机用二级混压式进气道压缩段设计方法研究  

Design Method of Two-Step Hypersonic Mixed Compression Inlet in Condensability Segment for TBCC Engine

作　　者：商旭升[1] 何宇峰 李垠广[1] 蔡飞超[3] 

机构地区：[1]海军装备研究院,北京100161 [2]空军跳伞运动大队,北京102206 [3]中国航天科工集团第三研究院,北京100074

出　　处：《推进技术》2015年第3期365-371,共7页Journal of Propulsion Technology

摘　　要：为了适应TBCC发动机宽马赫数进气需求,基于Oswatitsch的最佳波系理论和CFD技术,考虑变比热、激波与附面层干扰等因素的影响,分别选取飞行马赫数Ma=4,高度H=21300m和飞行马赫数Ma=6,高度H=26600m为设计点,对TBCC发动机二级混压式进气道进行了初步设计,分析并比较了两种方案进气道的设计点和非设计点性能及二维流场。计算结果表明:不考虑粘性影响,本文设计的进气道能够满足沿飞行轨迹的TBCC发动机性能要求,具有良好的内外流特性。In order to adapt the requirements of wide TBCC engine inlet Mach number, based on the best Oswatitsch wave theory and CFD technology, considering the influence of factors such as the variable specific heat, shock wave and boundary layer disturbance, the design points of the inlet are determined to be Ma=4, H=21300m and Ma=6, H=26600m. Two-step hypersonic mixed compression inlet of TBCC engine has been carried on the preliminary design, analysis and comparison for the performance of the two kinds of scheme at design points, non-design points and the two dimensional flow field. Calculation results indicate that without considering viscous effects, along the flight path, the inlet design can satisfy the TBCC performance requirements and the present inlet has the good internal and external flow features.

关 键 词：高超声速进气道 一体化 起动性能 变比热 TBCC发动机 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]