非对称来流下矩形转圆隔离段数值研究

发布时间：2018-01-27 05:13

本文关键词： 超燃冲压发动机隔离段矩形转圆非对称来流数值模拟　出处：《推进技术》2016年12期 　论文类型：期刊论文

【摘要】：针对采用超椭圆曲线方法设计的矩形转圆隔离段,在非对称来流条件下,利用数值模拟手段研究了出口反压、来流马赫数、进口附面层厚度等因素对其性能的影响。研究结果表明:出口反压与附面层相互作用导致初始激波形态转变为"λ"激波,并且隔离段的性能随着反压的增大而下降,低能流区域迅速增长,流场非对称效应逐渐变小;来流马赫数的增大会提高隔离段的抗反压能力,并且会降低流场的非对称效应,但出口总压恢复系数却随之下降,特别是与来流马赫数为2情况相比,当来流马赫数为2.5时其降低了7.2%;进口附面层厚度的增加会加剧隔离段内的流动分离,导致隔离段的抗反压能力降低,不利于隔离段出口流场品质,并且相对于均匀来流而言,当进口附面层无量纲厚度为0.33时出口总压恢复系数下降了13.7%。
[Abstract]:For the rectangular circular isolation section designed by the hyperelliptic curve method, under the condition of asymmetric flow, the outlet back pressure and the Mach number of incoming flow are studied by means of numerical simulation. The influence of the thickness of the inlet boundary layer on its performance. The results show that the initial shock wave morphology changes to "位" shock wave due to the interaction between the exit back pressure and the boundary layer. The performance of the isolation section decreases with the increase of the backpressure, and the low energy flow region increases rapidly, and the asymmetric effect of the flow field becomes smaller. The increase of the number of incoming Mach increases the anti-backpressure ability of the isolation section and reduces the asymmetric effect of the flow field, but the total pressure recovery coefficient of the outlet decreases, especially when the Mach number of the incoming flow is 2. When the Mach number is 2.5, the Mach number decreases by 7.2. The increase of the thickness of the inlet boundary layer will aggravate the flow separation in the isolation section, leading to the decrease of the anti-pressure ability of the isolation section, which is not conducive to the quality of the flow field at the outlet of the isolation section, and is relative to the uniform flow. When the dimensionless thickness of the inlet boundary layer is 0.33, the total pressure recovery coefficient of the outlet decreases by 13.7%.
【作者单位】：中国民航大学中欧航空工程师学院;南京航空航天大学能源与动力学院;
【基金】：中央高校基本项目(3122015Z001)
【分类号】：V231
【正文快照】： 2.南京航空航天大学能源与动力学院,江苏南京210016)1引言隔离段是超燃冲压发动机的重要组成部分之一,它主要在进气道与燃烧室之间起着气动热力缓冲段的作用。由于隔离段主要通过激波串来实现进气道与燃烧室之间的压力匹配,因此其内部流动十分复杂[1~3],主要表现为其内部的流

【相似文献】