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dc.contributor.advisorBogard, David G.en
dc.creatorDyson, Thomas Earlen
dc.date.accessioned2013-01-30T17:55:57Zen
dc.date.available2013-01-30T17:55:57Zen
dc.date.issued2012-12en
dc.date.submittedDecember 2012en
dc.identifier.urihttp://hdl.handle.net/2152/ETD-UT-2012-12-6743en
dc.descriptiontexten
dc.description.abstractThis study focused on the improvement of film cooling for gas turbine vanes using both computational and experimental techniques. The experimental component used a matched Biot number model to measure scaled surface temperature (overall effectiveness) distributions representative of engine conditions for two new configurations. One configuration consisted of a single row of holes on the pressure surface while the other used numerous film cooling holes over the entire vane including a showerhead. Both configurations used internal impingement cooling representative of a 1st vane. Adiabatic effectiveness was also measured. No previous studies had shown the effect of injection on the mean and fluctuating velocity profiles for the suction surface, so measurements were made at two locations immediately upstream of film cooling holes from the fully cooled cooling configuration. Different blowing conditions were evaluated. Computational tools are increasingly important in the design of advanced gas turbine engines and validation of these tools is required prior to integration into the design process. Two film cooling configurations were simulated and compared to past experimental work. Data from matched Biot number experiments was used to validate the overall effectiveness from conjugate simulations in addition to adiabatic effectiveness. A simulation of a single row of cooling holes on the suction side also gave additional insight into the interaction of film cooling jets with the thermal boundary layer. A showerhead configuration was also simulated. The final portion of this study sought to evaluate the performance of six RANS models (standard, realizable, and renormalization group k-ε; standard k-ω; k-ω SST; and Transition SST) with respect to the prediction of thermal boundary layers. The turbulent Prandtl number was varied to test a simple method for improvement of the thermal boundary layer predictions.en
dc.format.mimetypeapplication/pdfen
dc.language.isoengen
dc.subjectFilm coolingen
dc.subjectConjugateen
dc.subjectRANS CFDen
dc.subjectBoundary layersen
dc.titleExperimental and computational investigation of film cooling on a large scale C3X turbine vane including conjugate effectsen
dc.date.updated2013-01-30T17:56:23Zen
dc.identifier.slug2152/ETD-UT-2012-12-6743en
dc.contributor.committeeMemberBradshaw, Seanen
dc.contributor.committeeMemberMurthy, Jayathien
dc.contributor.committeeMemberRaman, Venkaten
dc.contributor.committeeMemberShi, Lien
dc.description.departmentMechanical Engineeringen
dc.type.genrethesisen
thesis.degree.departmentMechanical Engineeringen
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorUniversity of Texas at Austinen
thesis.degree.levelDoctoralen
thesis.degree.nameDoctor of Philosophyen


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