Effects of Realistic First-Stage Turbine Endwall Features

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dc.contributor.authorCardwell, Nicholas Donen
dc.contributor.committeechairThole, Karen A.en
dc.contributor.committeecochairO'Brien, Walter F. Jr.en
dc.contributor.committeememberVick, Brian L.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T20:49:30Zen
dc.date.adate2006-01-03en
dc.date.available2014-03-14T20:49:30Zen
dc.date.issued2005-12-09en
dc.date.rdate2006-01-03en
dc.date.sdate2005-12-14en
dc.description.abstractThe modern gas turbine engine requires innovative cooling techniques to protect its internal components from the harsh operating environment typically seen downstream of the combustor. Much research has been performed on the design of these cooling techniques thus allowing for combustion temperatures higher than the melting point of the parts within the turbine. As turbine inlet temperatures and efficiencies continue to increase, it becomes vitally important to correctly and realistically model all of the turbine's external cooling features so as to provide the most accurate representation of the associated heat transfer to the metal surfaces. This study examines the effect of several realistic endwall features for a turbine vane endwall. The first study addresses the effects of a mid-passage gap, endwall misalignment, and roughness on endwall film-cooling. The second study focuses on the effect of varying the combustor-to-turbine gap width. Both studies were performed in a large-scale low speed wind tunnel with the same vane geometry. Geometric and flow parameters were varied and the variation in endwall cooling effectiveness was evaluated. Results from these studies show that realistic features, such as surface roughness, can reduce the effectiveness of endwall cooling designs while other realistic features, such as varying the combustor-to-turbine gap width, can significantly improve endwall cooling effectiveness. It was found that, for a given coolant mass flowrate, a narrow combustor-turbine gap width greatly increased the coverage area of the leaked coolant, even increasing adiabatic effectiveness upstream of the vane stagnation point. The turbine designer can also more efficiently utilize leaked coolant from the combustor-to-turbine gap by controlling endwall misalignment, thereby reducing the overall amount of film-cooling needed for the first stage.en
dc.description.degreeMaster of Scienceen
dc.identifier.otheretd-12142005-142556en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-12142005-142556/en
dc.identifier.urihttp://hdl.handle.net/10919/36121en
dc.publisherVirginia Techen
dc.relation.haspartThesis_Cardwell.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectfilm-coolingen
dc.subjectvane endwallsen
dc.subjectsurface roughnessen
dc.subjectgas turbinesen
dc.titleEffects of Realistic First-Stage Turbine Endwall Featuresen
dc.typeThesisen
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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