爆震管喷管流动数值研究

推进技术 ›› 2009, Vol. 30 ›› Issue (3): 360-365.

爆震管喷管流动数值研究

孙孔倩,樊未军,杨茂林

北京航空航天大学航空发动机气动热力重点实验室;北京航空航天大学航空发动机气动热力重点实验室;北京航空航天大学航空发动机气动热力重点实验室

发布日期:2021-08-15

Numerical simulation of nozzle flow on detonation duct

National Key Laboratory on Aircraft Engine,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;National Key Laboratory on Aircraft Engine,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;National Key Laboratory on Aircraft Engine,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得高性能的爆震管,应用时空守恒元和解元(CE/SE)法对带不同形式喷管的爆震管进行二维轴对称数值模拟,分析复杂的爆震波流场,研究喷管对爆震管性能的影响。结果表明,爆震管的推进性能的提高受喷管的长度、夹角和形状的影响,其中长喷管性能优于短喷管,收敛扩张喷管性能优于收敛喷管,钟形喷管性能优于扩张喷管。

关键词: 爆震管;喷管;数值仿真

Abstract: In order to obtain the detonation duct of high performance,a space-time conservation element and solution element method(CE/SE) was used to simulate the formation and propagation process of two-dimensional axisymmetric detonation in duct with vairous nozzle,and analyze the complicated flow field,and studied the effect of nozzles on the duct.Results showed that the duct performance was effected by the length,angle and sharp of nozzle.The performance of long nozzle was better than that of the short one.The performance of convergent-divergent nozzle was better than that of convergent nozzle.The performace of bell nozzle was better than that of divergent nozzle.

Key words: Detonation duct;Nozzle;Numerical simulation

孙孔倩,樊未军,杨茂林. 爆震管喷管流动数值研究[J]. 推进技术, 2009, 30(3): 360-365.