Shock tube study of kerosene ignition delay at high pressures

Ignition delay times of China No. 3 aviation kerosene were measured behind reflected shock waves using a heated high-pressure shock tube. Experimental conditions covered a wider temperature range of 820–1500 K, at pressures of 5.5, 11 and 22 atm, equivalence ratios of 0.5, 1.0 and 1.5, and oxygen concentration of 20%. Adsorption of kerosene on the shock tube wall was taken into account. Ignition delay times were determined from the onset of the excited radical OH emission in conjunction with the pressure profiles. The experimental results of ignition delay time were correlated with the equations: τ = 3.2 × 10−11[Kerosene]0.22[O2]−1.09 exp(69941/RT) and τ = 4.72×10−7P−0.88ϕ0.23 exp(62092/RT). The current measurements provide the ignition delay behavior of China No. 3 aviation kerosene at high pressures and air-like O2 concentration.