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dc.contributor.authorAbraham, Santoshen_US
dc.date.accessioned2014-03-14T20:45:53Z
dc.date.available2014-03-14T20:45:53Z
dc.date.issued2008-08-29en_US
dc.identifier.otheretd-09242008-151620en_US
dc.identifier.urihttp://hdl.handle.net/10919/35177
dc.description.abstract(ABSTRACT) Combustion designers have considered back-side impingement cooling as the solution for modern DLE combustors. The idea is to provide more cooling to the deserved local hot spots and reserve unnecessary coolant air from local cold spots. Therefore, if accurate heat load distribution on the liners can be obtained, then an intelligent cooling system can be designed to focus more on the localized hot spots. The goal of this study is to determine the heat transfer and pressure distribution inside a typical can-annular gas turbine combustor. This is one of the first efforts in the public domain to investigate the convective heat load to combustor liner due to swirling flow generated by swirler nozzles. An experimental combustor test model was designed and fitted with a swirler nozzle provided by Solar Turbines Inc. Heat transfer and pressure distribution measurements were carried out along the combustor wall to determine the thermo-fluid dynamic effects inside a combustor. The temperature and heat transfer profile along the length of the combustor liner were determined and a heat transfer peak region was established. Constant-heat-flux boundary condition was established using two identical surface heaters, and the Infrared Thermal Imaging system was used to capture the real-time steady-state temperature distribution at the combustor liner wall. Analysis on the flow characteristics was also performed to compare the pressure distributions with the heat transfer results. The experiment was conducted at two different Reynolds numbers (Re 50,000 and Re 80,000), to investigate the effect of Reynolds Number on the heat transfer peak locations and pressure distributions. The results reveal that the heat transfer peak regions at both the Reynolds numbers occur at approximately the same location. The results from this study on a broader scale will help in understanding and predicting swirling flow effects on the local convective heat load to the combustor liner, thereby enabling the combustion engineer to design more effective cooling systems to improve combustor durability and performance.en_US
dc.publisherVirginia Techen_US
dc.relation.haspartAbraham_Thesis.pdfen_US
dc.rightsI hereby certify that, if appropriate, I have obtained and attached hereto a written permission statement from the owner(s) of each third party copyrighted matter to be included in my thesis, dissertation, or project report, allowing distribution as specified below. I certify that the version I submitted is the same as that approved by my advisory committee. I hereby grant to Virginia Tech or its agents the non-exclusive license to archive and make accessible, under the conditions specified below, my thesis, dissertation, or project report in whole or in part in all forms of media, now or hereafter known. I retain all other ownership rights to the copyright of the thesis, dissertation or project report. I also retain the right to use in future works (such as articles or books) all or part of this thesis, dissertation, or project report.en_US
dc.subjectDry Low Emission (DLE) combustorsen_US
dc.subjectInfrared Thermal Imagingen_US
dc.subjectSwirleren_US
dc.subjectCombustor liner cooingen_US
dc.titleHeat Transfer and Flow Measurements on a One-Scale Gas Turbine Can Combustor Modelen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical Engineeringen_US
thesis.degree.nameMaster of Scienceen_US
thesis.degree.levelmastersen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
dc.contributor.committeechairEkkad, Srinath V.en_US
dc.contributor.committeememberTafti, Danesh K.en_US
dc.contributor.committeememberVandsburger, Urien_US
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-09242008-151620/en_US
dc.date.sdate2008-09-24en_US
dc.date.rdate2008-11-05
dc.date.adate2008-11-05en_US


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