RP-3 航空煤油宽工况自点火实验及反应动力学模型验证

A new injection strategy for shock tube was proposed and verified systematically in this paper. The experimental results showed that the injection strategy can reproduce the experimental results of the traditional method of shock tube, and effectively broaden the self-ignition measurement range of low saturated vapor pressure fuels. The ignition delay time of RP-3 aviation kerosene and air mixture was measured at the temperature of 650∼1300 K, equivalent ratio of 0.5∼1.5 and pressure of 0.75∼3.0 MPa based on the shock tube injection strategy. It provided a broader basic data set for engine combustion chamber design and development and validation of RP-3 aviation kerosene surrogate fuel kinetic model. Finally, the reliability of the current RP-3 aviation kerosene surrogate models was assessed based on experimental data. The comparison results indicated that these models fail to accurately predict the self-ignition characteristics of RP-3 aviation kerosene under the full pressure range, especially in the area of the negative temperature coefficient where significant deviations were observed.