Experimental study of the combustion of surrogates of aviation kerosene TS-1

In the present study, two types of surrogate mixtures for kerosene suggested in the literature have been analyzed: the six-component SU1 and the four-component SU2, which characteristics differ from the accepted reference values by not more than 1%, except for the molecular weight of the surrogate SU2, which deviates by 3%. It was revealed that multi-component surrogates are required to reproduce physical-chemical properties of a real aviation kerosene. Moreover, different classes of hydrocarbons, such as alkanes, cyclic alkanes, and aromatics should be all included to match these properties. Other parameters, such as density, H/C ratio and molar mass, impose additional and important constraints on development of surrogates. Furthermore, the availability of detailed kinetic mechanisms capable to model new suggested surrogate mixtures was taken into account. It was experimentally demonstrated that the spray characteristics of both aviation kerosene TS-1 and surrogates SU1 and SU2 closely match in the studied range of pressure drops across the pressure-swirl atomizer. Burning velocities of the surrogates SU1 and SU2 have been measured using the heat flux method and have been successfully reproduced by the kinetic modeling using Polimi and JetSurF mechanisms, respectively. In a model combustion chamber, concentrations of main products of the kerosene TS-1 and surrogates SU1 and SU2 have been also measured. Good agreement was found for the main components of the products of complete combustion, O2 and CO2. The maximum deviation for carbon monoxide and unburned hydrocarbons did not exceed 10%.