Meyers, Bronwyn CGrobler, Jan-Hendrik2025-02-132025-02-132024-09http://hdl.handle.net/10204/14021A combustor design programme was initiated to design a combustor for a 200N microgas turbine. The method is that of a phased approach in order to gain better insight into the effect of various aspects of the combustor geometry as well as the combustor boundary conditions. The preliminary combustor design was performed using the NREC design method resulting in multiple designs to consider. This first phase focused on the Annuli mass flow splits and ensuring an improved Primary zone by devising a configuration conducive to a Recirculation zone approaching that shown in the theory. In order to make design selections, and later evaluate the effects of boundary conditions and design methods, a scoring and ranking method was devised to effectively evaluate the cold flow CFD simulation results. The second phase involved the evaluation of the effect of inlet swirling flow on the designs selected in phase one. This study, constituting phase three, is focused on the design of the Secondary and Dilution zone hole-sets using multiple methods available in literature, namely Lefebvre, Lefebvre and Ballal, and Mattingly et al. The purpose of this design phase is to improve the Secondary and Dilution zone holes. The resultant hole-sets were evaluated for practicality and manufacturability and adjustments were made to the number and size of the holes while maintaining a constant Total hole-set area (Aht) and attempting to maintain a constant Jet Diameter - Momentum flux ratio (djJ0.5). In addition to the design improvements, the aim is to compare four additional design methods and identify the preferred hole-set design method as well as to evaluate whether the applied adjustments maintain the penetration depths as was indicated should be the case in the literature. It was found that although the Lefebvre method produced some improved designs, it also produced many designs that were not improvements, thus it can not be said that the particular method is a better one. In addition, there weren’t highly evident trends that emerged with the systematic changes, thus a change in the combustor design approach could be beneficial which involves design through the optimisation of a complete parameter space to determine a better design per application or engine.FulltextenCombustorComputational Fluid DynamicsHole-set DesignConference PresentationN/A