Численное моделирование горения капель смеси керосин/изопропиловый спирт в камере сгорания авиационного ГТД

Abstract

This work presents the results of numerical modeling of combustion of kerosene/isopropyl alcohol droplets in the combustion chamber of an aircraft gas turbine engine. The numerical calculations of the combustion processes were performed using ANSYS Fluent. Aviation kerosene was modeled using a four-component surrogate, SU2, which was developed in the Engineering center of Samara University. One operation mode and three proportions of isopropyl alcohol additive were studied. The combustion processes were modeled using the Partially Premixed Combustion model, which includes the Flamelet Generated Manifold approach and the compilation of Probability Density Function tables. Fuel atomization by the pressure-swirl atomizer was modeled using the Discrete Phase Model. The addition of isopropyl alcohol to the mixture leads to a decrease in the temperature in the combustion chamber, which in turn leads to a decrease in NOx emissions by an average of 50%. The average droplet evaporation time first decreases by 50% with