RP-3航空煤油模拟替代燃料燃烧特性的实验

在定容弹中实验测试了初始压力分别为0.1、0.3 MPa、初始温度分别为390、400、420 K、当量比范围为0.8～1.5时RP-3航空煤油模拟替代燃料的层流燃烧特性,并对比分析了模拟替代燃料与RP-3航空煤油的层流燃烧速率。结果表明,模拟替代燃料层流燃烧火焰的马克斯坦长度随初始压力或当量比的降低逐渐增大,表明火焰稳定性逐步增强；初始温度对火焰稳定性的影响不明显；随初始温度的升高或初始压力的降低,模拟替代燃料的层流燃烧速率逐渐升高；随着当量比的逐渐增大,模拟替代燃料的层流燃烧速率先增大后降低,在当量比为1.2时达到最大；在相同工况下,模拟替代燃料与RP-3航空煤油的层流燃烧速率吻合较好。 

Experiment on combustion characteristics of surrogate fuel for RP-3 aviation kerosene

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.