An experimental and numerical study of heat transfer augmentation near the entrance to a film cooling hole

dc.contributor.advisorMorris, Reuben Montresoren
dc.contributor.advisorVisser, J.A.en
dc.contributor.emailgerard@qfin.neten
dc.contributor.postgraduateScheepers, Gerarden
dc.date.accessioned2013-09-07T11:49:12Z
dc.date.available2008-09-19en
dc.date.available2013-09-07T11:49:12Z
dc.date.created2008-04-18en
dc.date.issued2008-09-19en
dc.date.submitted2008-08-27en
dc.descriptionDissertation (MEng)--University of Pretoria, 2008.en
dc.description.abstractDevelopments regarding internal cooling techniques have allowed the operation of modern gas turbine engines at turbine inlet temperatures which exceed the metallurgical capability of the turbine blade. This has allowed the operation of engines at a higher thermal efficiency and lower specific fuel consumption. Modern turbine blade-cooling techniques rely on external film cooling to protect the outer surface of the blade from the hot gas path and internal cooling to remove thermal energy from the blade. Optimization of coolant performance and blade-life estimation require knowledge regarding the influence of cooling application on the blade inner and outer surface heat transfer. The following study describes a combined experimental and computational study of heat transfer augmentation near the entrance to a film-cooling hole. Steady-state heat transfer results were acquired by using a transient measurement technique in an 80 x actual rectangular channel, representing an internal cooling channel of a turbine blade. Platinum thin-film gauges were used to measure the inner surface heat transfer augmentation as a result of thermal boundary layer renewal and impingement near the entrance of a film-cooling hole. Measurements were taken at various suction ratios, extraction angles and wall temperature ratios with a main duct Reynolds number of 25×103. A numerical technique, based on the resolution of the unsteady conduction equation, using a Crank-Nicholson scheme, was used to obtain the surface heat flux from the measured surface temperature history. Computational data was generated with the use of a commercial CFD solver.en
dc.description.availabilityunrestricteden
dc.description.departmentMechanical and Aeronautical Engineeringen
dc.identifier.citationa 2007en
dc.identifier.otherE1066/gmen
dc.identifier.upetdurlhttp://upetd.up.ac.za/thesis/available/etd-08272008-163851/en
dc.identifier.urihttp://hdl.handle.net/2263/27590
dc.language.isoen
dc.publisherUniversity of Pretoriaen_ZA
dc.rights© University of Pretoria 2007 E1066/en
dc.subjectCoolant extractionen
dc.subjectComputational fluid dynamicsen
dc.subjectSuction ratioen
dc.subjectHeat transfer enhancementen
dc.subjectTurbine bladeen
dc.subjectFilm-coolingen
dc.subjectExtraction angleen
dc.subjectInternal coolingen
dc.subjectExtraction holeen
dc.subjectAugmentationen
dc.subjectUCTDen_US
dc.titleAn experimental and numerical study of heat transfer augmentation near the entrance to a film cooling holeen
dc.typeDissertationen

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