A swirler stabilized combustion chamber for a micro-gas turbine fuelled with natural gas

micro-gas turbines are a good alternative for on-site power generation, since their operation is very reliable. the possibility of operating with various fuels increases versatility and, as a result, the usage of these devices. focusing on a performance improvement of a tri-fuel low-cost micro-gas turbine, this work presents investigations of the inner flow of its combustion chamber. the aim of this analysis was the characterization of the flame structure by the temperature field of the chamber inner flow. the chamber was fuelled with natural gas. in the current chamber, a swirler and a reversed flow configuration were utilized to provide flame stabilization. the inner flow investigations were done with numerical analysis, which were compared to experimental data. the analysis of the inner flow was done with numerical simulations, which used the rsm turbulence model. a β-pdf equilibrium model was adopted to account for the turbulent combustion process. different models of heat transfer were compared. thermal radiation and specially heat conduction in the liner walls played significant roles on results.