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In this study, emissions from a surrogate of aviation fuel components have been characterized. The proposed surrogate includes n-dodecane and m-xylene with 75% and 25% by liquid volume, respectively. The combustion was investigated behind reflected shock waves to obtain ignition delay times and quantify yields of a range of stable combustion products including volatile gases, aldehydes, PAHs (polycyclic aromatic hydrocarbons) and soot. The experimental conditions covered a temperature range of ~980-1500 K, at pressures of 18 atm, at an equivalence ratio of 3, using argon as the diluent (93 % vol). In all experiments, dwell times were kept in the range of 7.55-7.85 ms by using a suitable argon-helium mixture as the driver gas. The collected gas samples from shock tube experiments were analyzed using GC-TCD for light gases and GC-MS was used for aldehydes, volatiles and semi-volatiles. The mass of the collected particulate matter (PM) was determined via the temperature programmed oxidation (TPO) / carbon burn-off method. The present work provides comprehensive emissions characterization data for the validation of combustion kinetic models, and valuable comparisons for selecting future alternate jet fuels based on their emissions

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Graduate Research

Primary Advisor

Sukhjinder S. Sidhu


Stander Symposium poster

Characterization of Emissions from the Combustion of a Selected Surrogate for Aviation Fuels