COMPUTATIONAL STUDY ON AERODYNAMIC CHARACTERISTICS OF AIRFLOW THROUGH A MICROTURBINE COMBUSTOR

Abstract

This study presents numerical findings pertaining to the aerodynamics of a novel microturbine combustor, with the aim of evaluating airflow organization for the combustion process. A CFD simulation method was employed, utilizing a geometric model derived from a developing microturbine design. The results indicate that the air mass flow is distributed as follows: 5% through the evaporator, 26% in the primary combustion zone, 34% in the secondary combustion zone, and 40% in the dilution zone, with respect to the total combustor airflow. The flow velocity remains below 0.3 Mach, and the total pressure loss is determined at 5.8%. The numerical results can be used as a foundation for adjusting and optimizing the combustor design before manufacturing.