帮助 关于我们

返回检索结果

不同直径圆球诱导燃烧的振荡机制与频率特性
Oscillation Mechanism and Frequency Characteristics of Combustion Induced by Spheres with Different Diameters

查看参考文献30篇

刘帅 1   张子健 2   滕宏辉 1 *  
文摘 为了分析不同直径圆球诱导振荡燃烧的规律,并揭示圆球大小在振荡燃烧现象中所发挥的深层次作用,采用二维轴对称Euler方程和基元反应模型,对不同直径的圆球在H2/air预混气体中诱导振荡燃烧的现象开展数值模拟研究。研究发现,振荡频率并不是简单地随直径增大而逐渐从高频向低频连续过渡,而是存在两次突变,形成了超高频、高频以及低频三种振荡燃烧模态。在两种模态间过渡时,振荡达到稳定状态前,会存在一段双频耦合的振荡阶段。三种不同振荡燃烧模态的产生是受到了不同振荡机制的作用,而两种模态间过渡时的双频耦合现象则是两种机制相互竞争的结果。
其他语种文摘 In order to analyze the law of oscillating combustion induced by spheres with different diameters and to reveal the inherent effect of sphere size on the oscillation phenomenon,numerical simulations are carried out to investigate the oscillating combustion phenomenon in a H2/air premixed gas mixture induced by spheres with different diameters,by solving the two-dimensional axisymmetric Euler equations along with a detailed combustion mechanism.Results show that as the sphere diameter increases,the frequency of oscillating combustion does not decrease continuously,but with two abrupt drops,which implies that there exist three modes in the high-speed sphere-induced oscillating combustion phenomenon,namely the superhigh-frequency mode,the high-frequency mode,and the low-frequency mode.During the transition of two modes,there exists a metastable oscillating state of double-frequency coupling before the oscillation reaches its stable state.Moreover,the appearance of these three different modes is affected by different oscillation mechanisms,and the double-frequency coupling phenomenon during the transition of two modes is resulted from the competition of two mechanisms.
来源 推进技术 ,2021,42(4):745-754 【核心库】
DOI 10.13675/j.cnki.tjjs.200245
关键词 激波诱导燃烧 ; 振荡燃烧 ; 频率特性 ; 高速圆球 ; 基元反应
地址

1. 北京理工大学宇航学院, 北京, 100081  

2. 中国科学院力学研究所, 北京, 100190

语种 中文
文献类型 研究性论文
ISSN 1001-4055
学科 力学
基金 国家自然科学基金
文献收藏号 CSCD:6939199

参考文献 共 30 共2页

1.  姜宗林. 爆轰推进概念与机理研究--新型发动机研究的热点. 世界科技研究与发展,2001,23(4) CSCD被引 2    
2.  Voland R T. X-43A Hypersonic Vehicle Technology Development. Acta Astronautica,2006,59(1/5):181-191 CSCD被引 40    
3.  Choi J. Unstable Combustion Induced by Oblique Shock Waves at the Non-Attaching Condition of the Oblique Detonation Wave. Proceedings of the Combustion Institute,2009,32(2) CSCD被引 12    
4.  Takayama kazuyoshi. Ram Accelerators. Proceedings of the Third International Workshop on Ram Accelerators,1997 CSCD被引 1    
5.  Lee J H S. The Detonation Phenomenon,2008 CSCD被引 67    
6.  Ruegg F W. A Missile Technique for the Study of Detonation Waves. Journal of Research of the National Bureau of Standards,Section C:Engineering and Instrumentation,1962 CSCD被引 1    
7.  Behrens H. Studies of Hypervelocity Firings into Mixtures of Hydrogen with Air or with Oxygen. Symposium (International) on Combustion,1965,10(1):245-252 CSCD被引 2    
8.  Lehr H F. Experiments on Shock-Induced Combustion. Astronautica Acta,1972,17:589-597 CSCD被引 34    
9.  McVey J B. Mechanisms of Instabilities of Exothermic Hypersonic Blunt-Body Flows,1968 CSCD被引 1    
10.  McVey J B. Mechanism of Instabilities of Exothermic Hypersonic Blunt-Body Flows. Combustion Science and Technology,1971,3(2):63-76 CSCD被引 7    
11.  Matsuo A. Numerical Simulation of Shock-Induced Combustion Around an Axisymmetric Blunt Body. 26th Thermophysics Conference,1991 CSCD被引 1    
12.  Matsuo A. Numerical Investigation of Oscillatory Instability in Shock-Induced Combustion around a Blunt Body. AIAA Journal,1993,31(10) CSCD被引 2    
13.  Matsuo A. Computational Study of Unsteady Combustion around Projectiles with Emphasis on the Large-Disturbance Oscillation. 32nd Aerospace Sciences Meeting and Exhibit,1994 CSCD被引 1    
14.  Sussman M. A Computational Study of Unsteady Shock-Induced Combustion of Hydrogen-Air Mixtures. 30th Joint Propulsion Conference and Exhibit,1994 CSCD被引 1    
15.  Ahuja J. Numerical Investigation of Shock-Induced Combustion Past Blunt Projectiles in Regular and Large-Disturbance Regimes. 33rd Aerospace Sciences Meeting and Exhibit,1995 CSCD被引 1    
16.  Ahuja J. Effects of Various Flow and Physical Parameters on Stability of Shock-Induced-Combustion. 34th Aerospace Sciences Meeting and Exhibit,1996 CSCD被引 1    
17.  Matsuo A. First Damkoehler Parameter for Prediction and Classification of Unsteady Combustions Around Hypersonic Projectiles. 32nd Joint Propulsion Conference and Exhibit,1996 CSCD被引 1    
18.  Kasahara J. Experimental Observation of Unsteady H_2-O_2 Combustion Phenomena Around Hypersonic Projectiles Using a Multiframe Camera. Symposium(International)on Com bustion,1996 CSCD被引 1    
19.  Matsuo A. Numerical Prediction of Envelope Oscillation Phenomena of Shock-Induced Combustion,1998 CSCD被引 1    
20.  Matsuo A. Prediction Method of Unsteady Combustion Around Hypersonic Projectile in Stoichiometric Hydrogen-Air. AIAA Journal,1998,36(10) CSCD被引 1    
引证文献 3

1 韩信 鼓包诱导斜爆震波的数值研究 推进技术,2022,43(5):200853
CSCD被引 8

2 刘思远 中心锥喷管喉道比参数对旋转爆轰燃烧影响的数值研究 推进技术,2023,44(9):2204071
CSCD被引 2

显示所有3篇文献

论文科学数据集
PlumX Metrics
相关文献

 作者相关
 关键词相关
 参考文献相关

版权所有 ©2008 中国科学院文献情报中心 制作维护:中国科学院文献情报中心
地址:北京中关村北四环西路33号 邮政编码:100190 联系电话:(010)82627496 E-mail:cscd@mail.las.ac.cn 京ICP备05002861号-4 | 京公网安备11010802043238号