Volume 35 Issue 8
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WANG Guangxu, TAN Yonghua, ZHUANG Fengchen. High frequency longitudinal combustion instability of modeled hypergolic propellants combustor,[J]. Journal of Aerospace Power, 2020, 35(8): 1578-1585. doi: 10.13224/j.cnki.jasp.2020.08.002
Citation: WANG Guangxu, TAN Yonghua, ZHUANG Fengchen. High frequency longitudinal combustion instability of modeled hypergolic propellants combustor,[J]. Journal of Aerospace Power, 2020, 35(8): 1578-1585. doi: 10.13224/j.cnki.jasp.2020.08.002
shu

High frequency longitudinal combustion instability of modeled hypergolic propellants combustor,

doi: 10.13224/j.cnki.jasp.2020.08.002
  • 1.

    National Key Laboratory of Science and Technology on Liquid Rocket Engines,Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Xi’an 710100,China

  • 2.

    Academy of Aerospace Propulsion Technology,China Aerospace Science and Technology Corporation,Xi’an 710100,China

  • 3.

    Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China

  • Received Date: 2020-01-09
  • Publish Date: 2020-08-28
    Abstract
  • High frequency longitudinal combustion instability of a modeled hypergolic propellants combustor was analyzed through concentrated combustion model, in which the distribution of droplet evaporation rate along flow axis was calculated. The peak position of evaporation rate was used as the position of concentrated combustion front when the chemical time was ignored and the empirical correlation of NASA was used to provide sensitive time and interaction index. Then the model for quantity analysis of high frequency longitudinal combustion instability was built considering the hypergolic propellants droplet evaporation. Based on the curves of system oscillation gain, stability tendency under different conditions of initial droplet radius and injection velocity was analyzed. It showed that the position of concentrated combustion front was critical to high frequency longitudinal combustion instability, improvement of averaged initial droplet radius and velocity could make the front far away from the injection face, and the corresponding oscillation gain could be reduced too, making the system more stable. Especially, when the averaged droplet radius got bigger than 150 μm, oscillation gain of the modeled combustor could be smaller than 10 and the combustor could become stable in theory.

     

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