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The preliminary design of an annular combustor for a mini gas turbine

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dc.contributor.author Meyers, Bronwyn C
dc.date.accessioned 2016-10-13T13:32:14Z
dc.date.available 2016-10-13T13:32:14Z
dc.date.issued 2015-10
dc.identifier.citation 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 en_US
dc.identifier.uri https://drc.libraries.uc.edu/bitstream/handle/2374.UC/745654/ISABE2015_CS%26A_Bronwyn%20Clara%20Meyers_241_MANUSCRIPT_20032.pdf?sequence=2
dc.identifier.uri http://hdl.handle.net/10204/8822
dc.description 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. en_US
dc.description.abstract 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. en_US
dc.language.iso en en_US
dc.relation.ispartofseries Worklist;15946
dc.subject Combustor liners en_US
dc.subject Mini gas turbines en_US
dc.subject Cape aerospace technologies en_US
dc.subject Northern research and engineering corporation en_US
dc.subject Air breathing engines en_US
dc.title The preliminary design of an annular combustor for a mini gas turbine en_US
dc.type Conference Presentation en_US
dc.identifier.apacitation Meyers, B. C. (2015). The preliminary design of an annular combustor for a mini gas turbine. http://hdl.handle.net/10204/8822 en_ZA
dc.identifier.chicagocitation Meyers, Bronwyn C. "The preliminary design of an annular combustor for a mini gas turbine." (2015): http://hdl.handle.net/10204/8822 en_ZA
dc.identifier.vancouvercitation Meyers BC, The preliminary design of an annular combustor for a mini gas turbine; 2015. http://hdl.handle.net/10204/8822 . en_ZA
dc.identifier.ris TY - Conference Presentation AU - Meyers, Bronwyn C AB - 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. DA - 2015-10 DB - ResearchSpace DP - CSIR KW - Combustor liners KW - Mini gas turbines KW - Cape aerospace technologies KW - Northern research and engineering corporation KW - Air breathing engines LK - https://researchspace.csir.co.za PY - 2015 T1 - The preliminary design of an annular combustor for a mini gas turbine TI - The preliminary design of an annular combustor for a mini gas turbine UR - http://hdl.handle.net/10204/8822 ER - en_ZA


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