This study involves the redesign of the combustor liner for a 200N mini gas turbine engine using first principles and the design methods of the NREC series as shown in Figure 1. The combustor design was performed using five different operating conditions as the input parameters. During the design process, some parts of the NREC process required modification due to the results being impractical or the requirements being different for a small engine compared to a typical gas turbine. The result of applying the procedure is 12 design options to choose from for the engine in question (CAT 200 KS). The multiple designs stem from either accepting certain compromises or variations in variables that are not dictated in the standard NREC design process.
Reference:
Meyers, B.C. 2015. The preliminary design of an annular combustor for a mini gas turbine. In: The preliminary design of an annular combustor for a mini gas turbine
Meyers, B. C. (2015). The preliminary design of an annular combustor for a mini gas turbine. http://hdl.handle.net/10204/8822
Meyers, Bronwyn C. "The preliminary design of an annular combustor for a mini gas turbine." (2015): http://hdl.handle.net/10204/8822
Meyers BC, The preliminary design of an annular combustor for a mini gas turbine; 2015. http://hdl.handle.net/10204/8822 .
The 22nd International Symposium on Air Breathing Engines (ISABE), Phoenix AZ United States, 25-30 October 2015. Due to copyright restrictions, the attached PDF file only contains the abstract of the full text item. For access to the full text item, please consult the publisher's website.
