环形脉冲爆震发动机引射性能

秦亚欣; 于军力; 高歌

环形脉冲爆震发动机引射性能

北京航空航天大学能源与动力工程学院航空发动机气动热力科技重点实验室,北京 100191

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出版历程
- 收稿日期: 2009-11-23
- 修回日期: 2010-05-13
- 刊出日期: 2011-01-28

Performance studies of annular pulse detonation engine ejectors

National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

摘要

摘要: 采用解析方法得出爆震波在爆震管内的参数分布,应用数值方法对爆震波衰退为激波后的传播、排除过程进行了多循环模拟.通过对环形爆震管非稳态引射过程的分析,得出非稳态引射过程可以分成四个阶段,环形爆震管比传统的圆形爆震管的引射作用更强.不同结构参数的引射喷管对环形爆震管的引射增推性能不同,经过分析,得到了较佳的引射喷管的入口尺寸、内表面形状、长度/直径比以及轴向位置,为提高脉冲爆震发动机的性能提供参考.
- 脉冲爆震发动机 /
- 爆震波 /
- 环形 /
- 引射 /
- 数值计算
Abstract: The distributions of detonation parameters in detonation chamber were gained by analytical numeration,and then multiple-cycle numerical simulations were carried out after detonation wave broke up to shock wave.The analysis on the mechanism of unsteady ejection shows that the process of unsteady ejection can be divided to four stages,and the ejection performance of annular pulse detonation duct is stronger than round pulse detonation duct.Different structures and parameters could induce different time-averaged thrust augmentations.The better shape of the ejector inlet,interior surface,ejector length-to-diameter ratio and axial placement were obtained through analysis,offering references to augment the performance of pulse detonation engine.
- pulse detonation engine /
- detonation wave /
- annular /
- ejection /
- numerical simulation

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参考文献(12)

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