«Previous Article|Table of Contents|Next Article»

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:

2008年04期

Page:

6-11

Research Field:

研究与设计

Publishing date:

Info

Title:

Investigation on the dynamic interaction between inj ector flow oscillation and combustion chamber pressure oscillation

Author(s):

Yang Lijun; Fu Qingfei

School of Astronautics，Beijing Univ．of Aeronautics and Astronautics，Beijing 100083，China

Keywords:

liquid rocket engine; injector; supply pipe-line; combustion chamber

PACS:

V434

DOI:

-

Abstract:

The propagation process of injector exit flow oscillation induced by combustion chamber pressure oscillation was theoretically researched，and the transfer function of the oscillation was also deduced．The dynamic characteristic of combustion chamber linked with various injectors was discussed．The influence of combustion chamber pressure，injector pressure drop，injector type and configuration on pressure oscillation propagation process was calculated，the influence rule of injector on propagation process was gained．

References:

[1]V．G．巴扎罗夫著．任汉芬，孙纪围译．液体喷嘴动力学 [M]．北京：中国宇航出版社。1997．
[2]Andreev气Bazarov V，Dushkin气et a1．Dynamics of Gas— Liquid Injector[M]．Moscow，Mashinostroenie，1991．
[3]Bazarov V，Yang Vigor．Liquid-Propellant rocket en矛ne inject dynamics[J]．Journal of propulsion power，V01．14． No．5，September-October 1998，PP．797—806．
[4]张向阳．液体离心喷嘴动态特性理论分析与数值模拟 [D]．北京：北京航空航天大学，2006．
[5]曹泰岳．火箭发动机动力学[M]．长沙：国防科技大学出 版社，200|4．266—276．
[6]杨立军，富庆飞．喷嘴对供应系统到燃烧室压力振荡传递 幅频特性的影响[J]．航空动力学报，2008，23(2)：305—310．
[7]D T Harrje著．朱宁昌，张宝炯译．液体推进剂火箭发 动机不稳定燃烧[M]．北京：国防工业出版社，1980．

Memo

Memo:

-

Common functions

Last Update: 1900-01-01