Abstract: A detailed mechanism for the combustion of n-decane, which is the single surrogate component of the Chinese aviation kerosene, was constructed by our program ReaxGen-Combustion for automatically generating reaction mechanisms of hydrocarbon fuels. Then referencing the observations of the Chinese aviation kerosene in the heating-up shock wave tube reactor, contrast studies were done on the reliability of the follo-wing models predicting the ignition delay behavior of gas-phase Chinese aviation kerosene: the three-component surrogate model(model Ⅰ), the two-component surrogate model(model Ⅱ), and the present single surrogate model(model Ⅲ). The results show that the ignition delay time predicted by model Ⅰ is in bad agreement with the observations during the temperature range of 1052-1538 K; model Ⅲ can give reasonable ignition delay time when the temperature is higher than 1176 K, but give results different from the observations in the range of 1052-1176 K; the ignition delay time predicted by model Ⅱ is close to those by model Ⅲ, however, the former takes the low-temperature mechanisms into account, so can give better results than model Ⅲ in the range of 1052-1176 K, though still different from the observations. In addition, the additive 20%(mass fraction) of 1,2,4-trimethylbenzene in model Ⅱ has little effect on the ignition delay time at high temperature.

Key words: n-Decane, Aviation kerosene, Chemical reaction kinetic mechanism, Ignition delay, Heated shock tube