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Journal of Projectiles, Rockets, Missiles and Guidance >

2019 , Vol. 39 >Issue 3: 163 - 167

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.03.036

Study on the Influence of Thermal Baffle Design Parameters on Vortex Acoustic Coupled Pressure Oscillation

  • ZHAO Xiaofeng ,
  • SUN Bingbing ,
  • LI Junqiang
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  • 1 Naval Equipment Department, Beijing 100000, China
    2 Xi'an Modern Chemistry Research Institute, Xi'an 710065, China

Received date: 2019-04-09

  Online published: 2025-05-20

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Abstract

In order to explore the influence of thermal baffle design parameters on the pressure oscillation characteristics caused by the vortex coupling effect, a numerical study was carried out based on the reduction model of the Ariane 5 launch vehicle engine. Firstly, the influence of the thermal baffle height on the pressure oscillation in the engine was studied. The results showed that the amplitude of the pressure oscillation increased gradually with the increase of the height of the thermal baffle. A reasonable design of thermal baffle height could reduce the pressure oscillation caused by vortex coupling. On this basis, the influence of the bending angle of the thermal baffle on the vortex coupled pressure oscillation was also studied, and it was found that the unstable mode of the pressure oscillation shifted from high mode to low mode with the increase of the bending angle of the thermal baffle. And the oscillation phenomenon gradually dispersed from the violent oscillation at a single frequency to the multi-frequency oscillation, reducing the maximum pressure oscillation range, which could reduce the damage of the pressure oscillation to a certain extent.

Key words： pressure oscillation; vortex-acoustic coupling; thermal baffle height; bending angle

Cite this article

ZHAO Xiaofeng , SUN Bingbing , LI Junqiang . Study on the Influence of Thermal Baffle Design Parameters on Vortex Acoustic Coupled Pressure Oscillation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019 , 39(3) : 163 -167 . DOI: 10.15892/j.cnki.djzdxb.2019.03.036

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References

[1]
STELLA F，PAGLIA F．Pressure oscillations in solid rocket motors: Numerical study[ J]．Aerospace Science and Technology，2011，15(1): 53-59．
[2]
FLANDRO G A，JACOBS H R．Vortex generated sound in cavities: AIAA 1973-1014[R]．Reston: AIAA，1973．
[3]
BROWN R S，DUNLAP R，YOUNG S W，et al．Vortex shedding as a source of acoustic energy in segmented solid rockets [J]．Journal of Spacecraft and Rockets，1981，18(4): 312-319．
[4]
ANTHOINE J．Experimental and Numerical Study of Aeroacoustic Phenomena in Large Solid Propellant Boosters: With Application to the Ariane 5 Solid Rocket Motor[D]．Brussels: Université Libre de Brussels，2000．
[5]
ANTHOINE J，LEMA M R．Passive control of pressure oscillations in solidrocket motors: cold-flow experiments[J]．Journal of Propulsion and Power，2009，25(3): 792-800．
[6]
李强，何国强，刘佩进，等．模型固体火箭发动机内涡脱落过程的大涡模拟[J]．推进技术，2005，26 (6): 481-484．
[7]
秦飞，何国强，刘佩进，等．同轴突扩燃烧室低频不稳定燃烧数值模拟[J]．推进技术，2008，29(4): 396-400．
[8]
张翔宇，何国强，刘佩进．轴对称后向台阶不稳定流动及压强振荡数值研究[J]．固体火箭技术，2012，35(2): 171-176．
[9]
王健儒，何国强，李强，等．分段式固体火箭发动机内部流动不稳定性数值分析[J]．推进技术，2013，34(1): 93-98．
[10]
许团委, 田维平, 王建儒. 结构特性对燃烧室压强振荡的影响研究[J].弹箭与制导学报,2013,33(1):117–120.
[11]
苏万兴. 大长径比固体火箭发动机不稳定燃烧预示及抑制方法研究[D]. 北京: 北京理工大学, 2015.
[12]
ZHANG Qiao, LI Junwei, WANG Weichen, et al. Numerical analysis on oscillation characteristics in a tail pipe nozzle solid rocket motor[J].Journal of Spacecraft and Rockets,2011,48(1):103-109.
[13]
VETEL J, PLOURDE F, DOAN-KIM S, et al. Cold gas simulations of the influence of inhibitor shape in combustor combustion[J].Journal of Propulsion and Power,2005,21(6):1098–1106.
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