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dc.contributor.authorBlot, Dorian Matthewen_US
dc.date.accessioned2013-02-19T22:41:10Z
dc.date.available2013-02-19T22:41:10Z
dc.date.issued2013-01-23en_US
dc.identifier.othervt_gsexam:159en_US
dc.identifier.urihttp://hdl.handle.net/10919/19257
dc.description.abstract     Endwall contouring has been widely studied as an effective measure to improve aerodynamic performance by reducing secondary flow strength. The effects of endwall contouring with discrete holes and an upstream purge slot for a high turning (127") airfoil passage under transonic conditions are investigated. The total pressure loss and secondary flow field were measured for two endwall geometries. The non-axisymmetric endwall was developed through an optimization study [1] to minimize secondary losses and is compared to a baseline planar endwall. The blade inlet span increased by 13 degrees with respect to the inlet in order to match engine representative inlet/exit Mach number loading in a HP turbine.  The experiments were performed in a quasi-2D linear cascade with measurements at design exit Mach number 0.88 and incidence angle. Four cases were analyzed for each endwall -- the effect of slot presence (with/without coolant) and the effect of discrete holes (with/without coolant) without slot injection. The coolant to mainstream mass flow ratio was set at 1.0% and 0.25% for upstream purge slot and discrete holes, respectively.  Aerodynamic loss coefficient is calculated with the measured exit total pressure at 0.1 Cax downstream of the blade trailing edge. CFD studies were conducted in compliment. The aero-optimized endwall yielded lower losses than baseline without the presence of the slot. However, in presence of the slot, losses increased due to formation of additional vortices. For both endwall geometries, results reveal that the slot has increased losses, while the addition of coolant further influences secondary flow development.en_US
dc.format.mediumETDen_US
dc.publisherVirginia Techen_US
dc.rightsThis Item is protected by copyright and/or related rights. Some uses of this Item may be deemed fair and permitted by law even without permission from the rights holder(s), or the rights holder(s) may have licensed the work for use under certain conditions. For other uses you need to obtain permission from the rights holder(s).en_US
dc.subjectGas Turbinesen_US
dc.subjectTransonic Cascadeen_US
dc.subjectAerodynamics. Heat Transferen_US
dc.subjectFilm Coolingen_US
dc.subjectUpstream Purge Sloten_US
dc.subjectDiscrete Hole Coolingen_US
dc.subjectEndwallen_US
dc.titleAerodynamics of Endwall Contouring with Discrete Holes and an Upstream Purge Slot Under Transonic Conditions  with and without Blowingen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical Engineeringen_US
dc.description.degreeMaster of Scienceen_US
thesis.degree.nameMaster of Scienceen_US
thesis.degree.levelmastersen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineMechanical Engineeringen_US
dc.contributor.committeechairEkkad, Srinath V.en_US
dc.contributor.committeechairNg, Wing Faien_US
dc.contributor.committeememberO'Brien, Walter F.en_US


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