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dc.contributor.authorLigrani, P.M.
dc.contributor.authorWilliam, W.
dc.date.accessioned2019-05-10T18:01:58Z
dc.date.available2019-05-10T18:01:58Z
dc.date.issued1989
dc.identifier.citationLigrani, P. M., and W. Williams. "Effects of an embedded vortex on injectant from a single film-cooling hole in a turbulent boundary layer." ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989.en_US
dc.identifier.urihttp://hdl.handle.net/10945/62169
dc.description.abstractEffects of embedded longitudinal vortices on heat transfer in turbulent boundary layers with injection from a single film cooling hole are described. These results were obtained at a freestream velocity of 10 m/s, with a film cooling hole inclined 30 degrees to horizontal and a blowing ratio of about 0.50. The ratio of vortex core diameter to injection hole diameter was 2.14, and the ratio of circulation to injection velocity times hole diameter was about 2.8. Coolant distributions and spatially resolved heat transfer measurements indicate that injection hole centerlines must be a least 2.0–2.5 vortex core diameters away from the vortex center in the lateral direction to avoid significant alterations to wall heat transfer and distributions of film coolant. Under these circumstances, protection from film cooling is evident at least up to 55 hole diameters downstream of injection. When the injection hole is closer to the vortex center, secondary flows convect most injectant into the vortex upwash and thermal protection from film cooling is destroyed for streamwise locations from the injection hole greater than 17.5 hole diameters.en_US
dc.description.sponsorshipNPS Research Foundationen_US
dc.format.extent11 p.en_US
dc.publisherASMEen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleEffects of an Embedded Vortex on Injectant from a Single Film-Cooling Hole in a Turbulent Boundary Layeren_US
dc.typeArticleen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US
dc.contributor.departmentMechanical Engineering
dc.description.funderAero-Propulsion Laboratory MIPR Number FY 1455-88-N0608.en_US


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