The combustion process within microturbine combustion chambers, characterized by numerous chemical reactions and internal vortex interactions, presents challenges in determining operational parameters. This study employs numerical methods to determine these parameters within the combustion chamber of a commercial Jetcat P130RX engine. By utilizing liquid fuel and discrete phase models in Ansys Fluent software, the numerical results closely approximate real-world conditions. The total pressure losses in non-reaction and reaction models are 6.34% and 5.81%, respectively. Flow rates distributed into the primary, secondary, and dilution zones are determined to be 26.24%, 19.83%, and 53.93%, respectively. The airflow entering the combustion chamber is divided into two streams: the first stream comprises 53.4% and the second stream comprises 43.6% of the total airflow. Within the first stream, 73% enters the combustion zone through the liner holes, while the remaining 27% enters the vaporizer. Within the second stream, 13% enters through the front holes, and 87% enters the combustion zone via the holes on the inner annular. The temperature field is relatively evenly distributed within 500–750 ℃. The highest outlet temperature is observed approximately one-third of the span from the inner diameter. These findings serve as crucial input parameters for experimental investigating the fuel-air mixture process in the vaporizer in subsequent research stages.