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由喷嘴连接的燃烧室到供应系统压力振荡传递过程研究
引用本文:杨立军,富庆飞.由喷嘴连接的燃烧室到供应系统压力振荡传递过程研究[J].航空动力学报,2009,24(5):1182-1186.
作者姓名:杨立军  富庆飞
作者单位:北京航空航天大学,宇航学院,北京,100191
基金项目:国家自然科学基金(50406007)
摘    要:为了研究在压力振荡由液体火箭发动机燃烧室传递到供应系统的过程中喷嘴所起的作用,从理论上分析了压力振荡由燃烧室到供应系统通过喷嘴的传递过程,推导了振荡传递过程的传递函数.讨论带有各种喷嘴的供应系统的动态特性,对供应系统管路长度、燃烧室压强、喷嘴种类、喷嘴压降及喷嘴结构尺寸对燃烧室压力振荡引起供应系统压力振荡的影响进行了计算,得到了喷嘴以及工况参数在传递过程中的影响规律.

关 键 词:液体火箭发动机  喷嘴  传递函数  燃烧室  供应系统
收稿时间:2008/4/29 0:00:00
修稿时间:2008/9/25 0:00:00

Investigation on pressure oscillation propagation from combustion chamber to pipeline through injector
YANG Li-jun and FU Qing-fei.Investigation on pressure oscillation propagation from combustion chamber to pipeline through injector[J].Journal of Aerospace Power,2009,24(5):1182-1186.
Authors:YANG Li-jun and FU Qing-fei
Institution:School of Astronautics;Beijing University of Aeronautics and Astronautics;Beijing 100191;China
Abstract:In order to investigate the effect of injector on pressure oscillation propagation from liquid rocket engine combustion chamber to pipe-line,the process of pressure oscillation propagation from combustion chamber to pipe-line was theoretically researched in this paper;and the transfer function was also deduced.The dynamic characteristic of pipe-line linked with various injectors was discussed.The influences of pipe-line length,combustion chamber pressure,injector type and configuration on pressure oscillati...
Keywords:liquid rocket engine  injector  transfer function  combustion chamber  pipe-line  
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