dc.contributor.author	Hohlfeld, Erik Max	en
dc.contributor.committeechair	Thole, Karen A.	en
dc.contributor.committeemember	Tafti, Danesh K.	en
dc.contributor.committeemember	Dancey, Clinton L.	en
dc.contributor.department	Mechanical Engineering	en
dc.date.accessioned	2017-04-04T19:49:12Z	en
dc.date.adate	2003-06-11	en
dc.date.available	2017-04-04T19:49:12Z	en
dc.date.issued	2003-05-08	en
dc.date.rdate	2016-09-30	en
dc.date.sdate	2003-05-19	en
dc.description.abstract	Turbine airfoils are exposed to the hottest temperatures in the gas turbine with temperatures typically exceeding the melting point of the blade material. Cooling methods investigated in this computational study included parasitic cooling flow losses, which are inherent to engines, and microcircuit channels. Parasitic losses included dirt purge holes, located along the blade tip, and platform leakage flow, which result from gaps between various turbine components. Microcircuits are a novel cooling technique involving small air passages placed near the airfoil surface to enhance internal cooling. This study evaluated the benefit of external film-cooling flow exhausted from strategically placed microcircuits. Along the blade tip, predictions showed mid-chord cooling was independent of the blowing from microcircuit exits. The formation of a pressure side vortex was found to develop for most microcircuit film-cooling cases. Significant leading edge cooling was obtained from coolant exiting from dirt purge holes with a small tip gap while little cooling was seen with a large tip gap. Along the blade platform, the migration of coolant from the front leakage was shown to cool a considerable part of the platform. Several hot spots were predicted along the platform, which were circumvented through the placement of microcircuit channels. Ingestion of hot mainstream gas was predicted along the aft portion of the gutter and agreed with distress exhibited by actual gas turbine engines.	en
dc.description.degree	Master of Science	en
dc.identifier.other	etd-05192003-115253	en
dc.identifier.sourceurl	http://scholar.lib.vt.edu/theses/available/etd-05192003-115253/	en
dc.identifier.uri	http://hdl.handle.net/10919/76781	en
dc.language.iso	en_US	en
dc.publisher	Virginia Tech	en
dc.rights	In Copyright	en
dc.rights.uri	http://rightsstatements.org/vocab/InC/1.0/	en
dc.subject	gas turbines	en
dc.subject	microcircuit	en
dc.subject	tip gap	en
dc.subject	platform	en
dc.subject	blade heat transfer	en
dc.subject	film-cooling	en
dc.title	Film Cooling Predictions Along the Tip and Platform of a Turbine Blade	en
dc.type	Thesis	en
dc.type.dcmitype	Text	en
thesis.degree.discipline	Mechanical Engineering	en
thesis.degree.grantor	Virginia Polytechnic Institute and State University	en
thesis.degree.level	masters	en
thesis.degree.name	Master of Science	en

Film Cooling Predictions Along the Tip and Platform of a Turbine Blade

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