Volume 34 Issue 12
Dec.  2019
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LIU Jing, HU Erjiang, HUANG Zuohua. Experiment on combustion characteristics of surrogate fuel for RP-3 aviation kerosene[J]. Journal of Aerospace Power, 2019, 34(12): 2677-2685. doi: 10.13224/j.cnki.jasp.2019.12.017
Citation: LIU Jing, HU Erjiang, HUANG Zuohua. Experiment on combustion characteristics of surrogate fuel for RP-3 aviation kerosene[J]. Journal of Aerospace Power, 2019, 34(12): 2677-2685. doi: 10.13224/j.cnki.jasp.2019.12.017
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Experiment on combustion characteristics of surrogate fuel for RP-3 aviation kerosene

doi: 10.13224/j.cnki.jasp.2019.12.017

  • State Key Laboratory of Multiphase Flow in Power Engineering,School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China

  • Received Date: 2019-06-09
  • Publish Date: 2019-12-28
    Abstract
  • The laminar combustion characteristics of surrogate fuel for RP-3 aviation kerosene were investigated experimentally in a constant volume bomb. The experiments were performed at initial pressures of 0.1, 0.3 MPa, initial temperatures of 390, 400, 420 K, and over the equivalence ratio range of 0.8-1.5. Furthermore, the laminar combustion velocities of the surrogate fuel and RP-3 aviation kerosene were contrastively analyzed. Results showed that decreasing the initial pressure or equivalence ratio increased the stability of the flame front, which was established by increased Markstein length. The effect of the initial temperature on the Markstein length was not clear. Increasing the initial temperature or decreasing the initial pressure led to an increase in the laminar combustion velocity of the surrogate fuel. With the increase of equivalence ratio, the laminar combustion velocity illustrated an increase initially and then decreased gradually, and the highest value was measured at the equivalence ratio was 1.2. Furthermore, the laminar combustion velocity of the surrogate fuel agreed well with that of RP-3 aviation kerosene under the same conditions.

     

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