声学扰动对燃烧室声学特性的影响研究

推进技术 ›› 2016, Vol. 37 ›› Issue (2): 201-208.

• 总体与系统 • 下一篇

声学扰动对燃烧室声学特性的影响研究

薛帅杰,洪流,杨伟东

西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100

发布日期:2021-08-15

Effects of Acoustic Excitation on Acoustic Characteristics for Combustor

Xi’an Aerospace Propulsion Institute，Laboratory of Science and Technology on Liquid Propulsion Rocket Engine，Xi’an 710100，China,Xi’an Aerospace Propulsion Institute，Laboratory of Science and Technology on Liquid Propulsion Rocket Engine，Xi’an 710100，China and Xi’an Aerospace Propulsion Institute，Laboratory of Science and Technology on Liquid Propulsion Rocket Engine，Xi’an 710100，China

Published:2021-08-15

摘要/Abstract

摘要： 针对利用旋转齿轮对燃烧过程施加高频声学扰动的方法，为获得其对同轴离心喷嘴燃烧室声学特性的影响，设计了一种带辅喷管的单喷嘴扁平燃烧室，分别在冷试和热试工况下研究了旋转齿轮声学扰动装置对燃烧室声学特性的影响。冷试中当扰动频率等于燃烧室某振型的特征频率时燃烧室内出现驻波特征振荡。热试重点关注了煤油蒸气/富氧空气燃烧过程对声学扰动的响应，改变扰动装置的位置可改变声压波节线的方向，实现推进剂喷入位置为声压波腹或声压波节。研究表明，一阶切向声学振荡对同轴离心喷嘴与声压波腹的相对位置敏感，煤油蒸气/富氧空气燃烧过程易受声压波动的影响，推测液氧煤油补燃循环发动机内的高频燃烧不稳定性可能易被声压波动激发。

关键词: 声学扰动；高频燃烧不稳定性；同轴离心喷嘴；声学特性

Abstract: In order to acquire effects of spinning wheel acoustic excitation on acoustic characteristics of combustor with coaxial swirl injectors，a flat combustor with a single coaxial swirl injector and an additional exhaust nozzle was developed. A test campaign including cold flow tests and hot fire tests was performed. In cold flow tests，when excitation frequency equalled to eigenfrequency，staying wave oscillations were excited. Hot fire tests were focused on the response of oxygen-enriched air/hot kerosene vapor combustion to acoustic pressure and velocity fluctuations. The orientation of acoustic pressure node line could be changed by changing the position of the excitation equipment. Then propellant could be injected into the position of a pressure node or anti-node. Tests results show that the first tangential mode was sensitive to the relative position between the coaxial swirl injector and the pressure anti-node. And oxygen-enriched air/hot kerosene vapor combustion was sensitive to acoustic pressure fluctuations. High frequency combustion instability for LOx/kerosene staged combustor may be sensitive to acoustic pressure fluctuations，too.

Key words: Acoustic excitation；High frequency combustion instability；Coaxial swirl injector；Acoustic characteristics

薛帅杰,洪流,杨伟东. 声学扰动对燃烧室声学特性的影响研究[J]. 推进技术, 2016, 37(2): 201-208.

XUE Shuai-jie,HONG Liu,YANG Wei-dong. Effects of Acoustic Excitation on Acoustic Characteristics for Combustor[J]. Journal of Propulsion Technology, 2016, 37(2): 201-208.

参考文献

[1] 杨 V, 安德松 W E. 液体火箭发动机燃烧不稳定性[M]. 张宝炯, 洪鑫译. 北京:科学出版社, 2001.
[2] Lecourt R, Foucaud R. Experiments on Stability of Liquid Propellant Rocket Motors[R]. AIAA 87-1772.
[3] Hardi J S, Martinez H C, Oschwald M, et al. LOx Jet Atomization Under Transverse Acoustic Oscillations[J].Journal of Propulsion and Power, 2014, 30(2): 337-349.
[4] Knapp B, Oschwald M. High Speed Visualization of Flame Response in a LOx/H2 Combustion Chamber During External Excitation[C]. Gottingen: 12th International Symposium on Flow Visualization, 2006.
[5] Knapp B, Farago Z, Oschwald M. Interaction of LOx/GH2 Spray-Combustion with Acoustic[R]. AIAA 2007-0572.
[6] Hardi J, Martinez H, Oschwald M. LOx Jet Atomization Under Transverse Acoustic Oscillations[J]. Journal of Propulsion and Power, 2014, 30(2): 337-349.
[7] Sliphorst M, Groening S, Knapp B, et al. Combustion Instability Coupling Mechanisms Between Acoustic and LOx/CH4 Spray Flames[R]. AIAA 2011-327.
[8] Sliphorst M. High Frequency Combustion Instabilities of LOx/CH4 Spray Flame s in Rocket Engine Combustion Chambers[D]. Delft: Technische Universiteit Delft, 2011.
[9] Rey C, Ducruix S, Richecoeur F, et al. High Frequency Combustion Instabilities Associated with Collective Interactions in Liquid Propulsion[R]. AIAA 2004-3518.
[10] Richecoeur F, Scouflaire P, Ducruix S, et al. High-Frequency Transverse Acoustic Coupling in a Multiple-Injector Cryogenic Combustor[J]. Journal of Propulsion and Power, 2006, 22(4): 790-799.
[11] 洪流, Fusetti A, Rosa M D, et al. 液氧/甲烷火焰和燃烧不稳定性试验[J]. 推进技术, 2007, 28(2):127-131. (HONG Liu, Fusetti A, Rosa M D, et al. Experimental Investigation on Combustion Instability of Liquid Oxygen and Methane Flame[J]. Journal of Propulsion Technology, 2007, 28(2):127-131.)
[12] McManus K, Poinsot T, Candel S. A Review of Active Control of Combustion Instabilities[J]. Progress in Energy and Combustion Science, 1993, 19: 1-29.
[13] Ghost A, Diao Q, Yu K H. Effects of Fuel Density, Velocity, and Composition on Flame-Acoustic Interaction[R]. AIAA 2007-570.
[14] Ghost A, Diao D, Young G, et al. Experimental Investigation of Shear-Coaxial Injector Flame Stability on Flow Parameters[R]. AIAA 2007-5569.
[15] Diao Q, Ghosh A, Yu K H. Acoustic Stability of Model Injector Flames Using H2-CH4 Fuel Mixture[R]. AIAA 2008-5251.
[16] Davis D, Chehroudi B. The Effects of Pressure and Acoustic Field on a Cryogenic Coaxial Jet[R]. AIAA 2004-1330.
[17] Leyva I A, Chehroudi B, Talley D. Dark Core Analysis of Coaxial Injectors at Sub-, Near-, and Supercritical Pressures in a Transverse Acoustic Field[R]. AIAA 2007-5456.
[18] Leyva I A, Rodriguez J I, Chehroudi B, et al. Preliminary Results on Coaxial Jets Spread Angles and the Effects of Variable Phase Transverse Acoustic Fields[R]. AIAA 2008-950.
[19] Oschwald M, Farago Z. Resonance Frequencies and Damping of a Combustor Acoustically Coupled to an Absorber[J]. Journal of Propulsion and Power, 2008, 24(3): 524-533.
[20] 张蒙正. 燃烧不稳定性模拟实验技术[M]. 西安:西北工业大学出版社, 2009.
[21] 王枫, 李龙飞, 张贵田. 液氧煤油补燃发动机喷注器高频燃烧不稳定性的试验研究[J]. 宇航学报, 2012, 33(2): 260-264.
[22] 刘国球. 液体火箭发动机原理[M]. 北京:中国宇航出版社, 1993.
[23] 杜功焕, 朱哲民, 龚秀芬. 声学基础[M]. 南京:南京大学出版社, 2001.
[24] 薛帅杰, 杨伟东, 洪流. 声学波管对圆柱燃烧室声学特性影响研究[C]. 安康:中国宇航学会第六届液体火箭推进专业委员会第二次会议, 2014.
[25] 哈杰 D T, 里尔登 F H. 液体推进剂发动机不稳定燃烧[M]. 朱昌宁, 张宝炯译. 北京:国防工业出版社, 1980.(编辑:梅瑛)

声学扰动对燃烧室声学特性的影响研究

Effects of Acoustic Excitation on Acoustic Characteristics for Combustor

PDF

可视化

被引次数

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价