On the method for hot-fire modeling of high-frequency combustion instability in liquid rocket engines

被引:11
|
作者
Sohn, CH [1 ]
Seol, WS
Shibanov, AA
Pikalov, VP
机构
[1] Chosun Univ, Dept Aerosp Engn, Kwangju 501759, South Korea
[2] Korea Aerosp Res Inst, Rocket Engine Dept, Taejon 305600, South Korea
[3] Res Inst Chem Machine Bldg, NIICHIMMASH, Sergiev Posad, Russia
来源
KSME INTERNATIONAL JOURNAL | 2004年 / 18卷 / 06期
关键词
scaling; combustion instability modeling; stability boundary; injector screening; model combustion chamber;
D O I
10.1007/BF02990873
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
This study presents the methodological aspects of combustion instability modeling and provides the numerical results of the model (sub-scale) combustion chamber, regarding geometrical dimensions and operating conditions, which are for determining the combustion stability boundaries using the model chamber. An approach to determine the stability limits and acoustic characteristics of injectors is described intensively. Procedures for extrapolation of the model operating parameters to the actual conditions are presented, which allow the hot-fire test data to be presented by parameters of the combustion chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for designers. Tests with the model chamber, based on the suggested scaling method, are far more cost-effective than with the actual (full-scale) chamber and useful for injector screening at the initial stage of the combustor development in a viewpoint of combustion instabilities.
引用
收藏
页码:1010 / 1018
页数:9
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