dc.contributor.author |
Meyers, Bronwyn C
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dc.date.accessioned |
2016-10-13T13:32:14Z |
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dc.date.available |
2016-10-13T13:32:14Z |
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dc.date.issued |
2015-10 |
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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
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dc.identifier.uri |
http://hdl.handle.net/10204/8822
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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 |
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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 -
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en_ZA |