| Citation: | ZHANG Ya，PAN Gang，DING Zhaobo，et al.Analysis and calculation of acoustic frequency of swirl injector in hot⁃fire testing［J］.Journal of Aerospace Power，2022，37（7）：1478‑1486. doi: 10.13224/j.cnki.jasp.20210416
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The high frequency pressure oscillation data of a hydrogen⁃oxygen preburner with swirl injectors in hot⁃fire testing were analyzed.The change trend of the frequency and associated testing parameters were compared.It was found that，the testing frequency of hot⁃fire testing may be influenced inherently by the sound speed of liquid film within the injector and the pressure of the combustion chamber.A semi⁃empirical formula based on acoustic theory was developed for swirl injector.The acoustic frequency calculated by using the data of pre⁃injection pressure and modified liquid oxygen temperature for sound speed agreed well with the measured data.It was believed that the semi⁃empirical formula similar to the acoustic frequency calculation of pipeline can be applied to swirl injector.The acoustic frequency determined the initial value of the dominant surface wave length of the liquid film in the swirl injector.The gas resistance of the dominant surface wave flow increased with the increasing pressure and liquid film velocity，which reduced the wavelength and increased the frequency of the first breaking of the liquid film，may be the influence mechanism of the positive correlation between the hot⁃fire testing frequency and the combustion chamber pressure.
| [1] |
RAYLEIGH J W S.The explanation of certain acoustical phenomena[J].Nature,1878,18（7）:319⁃321.
|
| [2] |
LUX J,HAIDN O.Effect of recess in high pressure liquid oxygen/methane coaxial injection and combustion[J].Journal of Propulsion and Power,2009,25（1）:24⁃32.
|
| [3] |
ARMBRUSTER W,HARDI J S,SUSLOV D，et al.Experimental investigation of self⁃excited com⁃bustion instabilities with injection coupling in a cryo⁃genic rocket combustor[J].Acta Astronautica,2018,151（6）:655⁃667.
|
| [4] |
巴扎罗夫 V G.液体喷嘴动力学[M].任汉芬,孙纪国，译.北京:中国宇航出版社,1997.
|
| [5] |
BAZAROV V G,YANG V.Liquid propellant rocket engine injectors dynamics[J].Journal of Propulsion and Power,1998,14（5）:797⁃806.
|
| [6] |
杨立军，张向阳，葛明和.敞口型离心喷嘴动力学特性理论分析[J].推进技术,2006,27（6）:497⁃500.
YANG Lijun,ZHANG Xiangyang,GE Minghe.Theoretical analysis of dynamics of open swirl injector[J].Journal of Propulsion Technology,2006,27（6）:497⁃500.（in Chinese）
|
| [7] |
杨立军，富庆飞，王永涛，等.多排切向通道敞口型离心喷嘴的动态特性研究[J].宇航学报,2006,27（5）:865⁃870.
YANG Lijun,FU Qingfei,WANG Yongtao,et al.Investigation of dynamic of multi⁃row tangential channel opened swirl injector[J].Journal of Astronautics,2006,27（5）:865⁃870.（in Chinese）
|
| [8] |
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.
YANG Lijun,FU Qingfei.Effect of injector on pressure oscil⁃lation amplitude frequency characteristics from pipeline to combustion chamber[J].Journal of Aerospace Power,2008,23（2）:305⁃310.（in Chinese）
|
| [9] |
杨立军，富庆飞，张向阳，等.结构参数对敞口型离心喷嘴动态特性的影响[J].航空动力学报,2007,22（6）:864⁃868.
YANG Lijun,FU Qingfei,ZHANG Xiangyang,et al.Study on in⁃fluence of configuration parameter of open end swirl in⁃jector on its dynamics[J].Journal of Aerospace Power,2007,22（6）:864⁃868.（in Chinese）
|
| [10] |
杨立军,葛明和,张向阳.液体离心喷嘴喷雾场动态特性的初步研究[J].航空动力学报,2005,20（6）:1083⁃1087.
YANG Lijun,GE Minghe,ZHANG Xiangyang.Preliminary investigation on dynamic characteristics of swirl injector[J].Journal of Aerospace Power,2005,20（6）:1083⁃1087.（in Chinese）
|
| [11] |
富庆飞,杨立军,屈元元，等.气液同轴喷嘴缩进室动态特性均相流模型[J].航空动力学报,2010,25（8）:1918⁃1922.
FU Qingfei,YANG Lijun,QU Yuanyuan,et al.Investigation on dynamic characteristic of recessed region of a gas⁃liquid coaxial injector with homogeneous flow model[J].Journal of Aerospace Power,2010,25（8）:1918⁃1922.（in Chinese）
|
| [12] |
FU Q F,YANG L J,WANG X D.Theoretical and experi⁃mental study of the dynamics of a liquid swirl injector[J].Journal of Propulsion and Power,2010,26（1）:94⁃101.
|
| [13] |
ZONG N,YANG V.Dynamics of simplex swirl inject or s for cryogenic propellants at supercritical conditions[R].AIAA 2004⁃1332,2004.
|
| [14] |
ZONG N,YANG V.Super critical fluid dynamics of pres⁃sure swirl injector with external excitations[R].AIAA 2007⁃5458,2007.
|
| [15] |
HUO H F,ZONG N,YANG V.Cryogenic fluid dynamic response of swirl injector to external forcing at super⁃critical conditions[R].AIAA 2009⁃233,2009.
|
| [16] |
富庆飞,杨立军,屈元元，等.敞口型液体离心喷嘴动态特性数值模拟[J].航空动力学报,2010,25（9）:2132⁃2138.
FU Qingfei,YANG Lijun,QU Yuanyuan,et al.Numerical simula⁃tion of dynamic characteristics of an open⁃end swirl in‑jector[J].Journal of Aerospace Power,2010,25（9）:2132⁃2138.（in Chinese）
|
| [17] |
BAI X,LI Q L,CHENG P,et al.Investigation of self⁃pulsation characteristics for a liquid⁃centered swirl coaxial injector with recess[J].Acta Astronautica,2018,151（7）:511⁃521.
|
| [18] |
IM J H,YOUNGBIN Y,BAZAROV V G.Experimental study on self⁃pulsation a gas/liquid swirl coaxial injector in high pressure envi⁃ronment[R].Daejeon,Korea:60th International Astronautical Congress,2009.
|
| [19] |
JOHN T,HEISTER S D.Numerical simulations of liquid rocket coaxial injector hydrodynamics[J].Journal of Propulsion and Power,2011,27（4）:793⁃810.
|
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