Vortex Combustion Chamber with Angular Flame Stabilizer: Design and Experimental Investigations

The combustion chamber has a significant impact on the gas turbine engines efficiency. Special attention is paid to the improvement of combustion chamber design. The design of the vortex combustion chamber was performed as part of the ongoing research aimed at ensuring a minimum level of temperature non-uniformity at the gas turbine inlet. After determining the inlet geometry of the vortex combustion chamber with angular flame stabilizer, the discrete cannular-type outlet geometry was designed. Numerical simulations showed that discrete outlet configuration provide a 33% reduction in radial non-uniformity was observed relative to a conventional gas turbine engine combustion chamber. The computational methodology was verified by comparing the results of numerical simulation with the results of hydrodynamic studies and with the results of bench tests on a quantitative and qualitative levels. As a further development of the vortex combustion chamber with angular flame stabilizer, a continuous outlet concept was proposed. The analysis of the temperature field showed a further decrease in the level of temperature non-uniformity with a continuous outlet.