A combustor was designed for a 200N micro-gas turbine [1, 2] using the NREC preliminary combustor design method [1, 2, 3]. During the design process, there are various aspects where there are no definitive methodologies for specifying the design detail, such as the design of the hole-sets, and multiple options can be derived that can satisfy the required mass flow split and pressure drop for a particular hole-set.
Reference:
Meyers, B.C., Grobler, J.H. & Snedden, G. 2023. An aerodynamic CFD analysis of inlet swirl in a micro-gas turbine combustor. http://hdl.handle.net/10204/13375 .
Meyers, B. C., Grobler, J. H., & Snedden, G. (2023). An aerodynamic CFD analysis of inlet swirl in a micro-gas turbine combustor. http://hdl.handle.net/10204/13375
Meyers, Bronwyn C, Jan H Grobler, and GC Snedden. "An aerodynamic CFD analysis of inlet swirl in a micro-gas turbine combustor." 2023 The Aeronautical Society of South Africa's Annual Conference, ICC, Pretoria, South Africa, 27 – 28 July 2023 (2023): http://hdl.handle.net/10204/13375
Meyers BC, Grobler JH, Snedden G, An aerodynamic CFD analysis of inlet swirl in a micro-gas turbine combustor; 2023. http://hdl.handle.net/10204/13375 .
