dc.contributor.author |
Meyers, BC
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|
dc.contributor.author |
Snedden, Glen C
|
|
dc.contributor.author |
Meyers, Bronwyn C
|
|
dc.contributor.author |
Roos, TH
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|
dc.contributor.author |
Mahmood, GI
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|
dc.date.accessioned |
2011-11-25T08:29:06Z |
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dc.date.available |
2011-11-25T08:29:06Z |
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dc.date.issued |
2011-09 |
|
dc.identifier.citation |
Meyers, BC, Snedden, GC, Meyer, JP et al. 2011. Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor. International Symposium on Air Breathing Engines, Gothenburg, Sweden, September 12-16, 2011 |
en_US |
dc.identifier.isbn |
978-1-60086-895-5 |
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dc.identifier.uri |
http://hdl.handle.net/10204/5338
|
|
dc.description |
International Symposium on Air Breathing Engines, Gothenburg, Sweden, September 12-16, 2011 |
en_US |
dc.description.abstract |
A three-component flow field inside a can-type, forward flow experimental combustor was measured under non-reacting conditions. The combustor was run at atmospheric conditions with the air flow supplied from a fan and the outlet was straight to atmosphere. Temperature data, under reacting conditions, in the combustor was also obtained using a thermocouple rake as well as an outlet velocity profile using a Pitot tube at reacting and non-reacting conditions. For the flowfield measurements a stereoscopic PIV system was used to measure the flow field data thus an optically accessible combustor was required. The combustor for these experiments was manufactured out of Perspex and thus only nonreacting experiments could be performed. This combustor was a replica of the metal combustor used for the reacting experiments except for the slightly thicker walls. |
en_US |
dc.language.iso |
en |
en_US |
dc.publisher |
American Institute of Aeronautics and Astronautics |
en_US |
dc.relation.ispartofseries |
Workflow request;7595 |
|
dc.subject |
Gas turbine combustor |
en_US |
dc.subject |
Particle image velocimetry |
en_US |
dc.subject |
Velocity |
en_US |
dc.subject |
Temperature |
en_US |
dc.subject |
Air breathing engines |
en_US |
dc.title |
Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor |
en_US |
dc.type |
Conference Presentation |
en_US |
dc.identifier.apacitation |
Meyers, B., Snedden, G. C., Meyers, B. C., Roos, T., & Mahmood, G. (2011). Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor. American Institute of Aeronautics and Astronautics. http://hdl.handle.net/10204/5338 |
en_ZA |
dc.identifier.chicagocitation |
Meyers, BC, Glen C Snedden, Bronwyn C Meyers, TH Roos, and GI Mahmood. "Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor." (2011): http://hdl.handle.net/10204/5338 |
en_ZA |
dc.identifier.vancouvercitation |
Meyers B, Snedden GC, Meyers BC, Roos T, Mahmood G, Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor; American Institute of Aeronautics and Astronautics; 2011. http://hdl.handle.net/10204/5338 . |
en_ZA |
dc.identifier.ris |
TY - Conference Presentation
AU - Meyers, BC
AU - Snedden, Glen C
AU - Meyers, Bronwyn C
AU - Roos, TH
AU - Mahmood, GI
AB - A three-component flow field inside a can-type, forward flow experimental combustor was measured under non-reacting conditions. The combustor was run at atmospheric conditions with the air flow supplied from a fan and the outlet was straight to atmosphere. Temperature data, under reacting conditions, in the combustor was also obtained using a thermocouple rake as well as an outlet velocity profile using a Pitot tube at reacting and non-reacting conditions. For the flowfield measurements a stereoscopic PIV system was used to measure the flow field data thus an optically accessible combustor was required. The combustor for these experiments was manufactured out of Perspex and thus only nonreacting experiments could be performed. This combustor was a replica of the metal combustor used for the reacting experiments except for the slightly thicker walls.
DA - 2011-09
DB - ResearchSpace
DP - CSIR
KW - Gas turbine combustor
KW - Particle image velocimetry
KW - Velocity
KW - Temperature
KW - Air breathing engines
LK - https://researchspace.csir.co.za
PY - 2011
SM - 978-1-60086-895-5
T1 - Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor
TI - Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor
UR - http://hdl.handle.net/10204/5338
ER -
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en_ZA |