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dc.contributor.authorWeigand, Bernhardde
dc.contributor.authorHarasgama, Sriwickrama P.de
dc.date.accessioned2012-02-02de
dc.date.accessioned2016-03-31T11:44:30Z-
dc.date.available2012-02-02de
dc.date.available2016-03-31T11:44:30Z-
dc.date.issued1994de
dc.identifier.other368508757de
dc.identifier.urihttp://nbn-resolving.de/urn:nbn:de:bsz:93-opus-70471de
dc.identifier.urihttp://elib.uni-stuttgart.de/handle/11682/7894-
dc.identifier.urihttp://dx.doi.org/10.18419/opus-7877-
dc.description.abstractA numerical investigation of film cooling on a turbine rotor blade has been carried out. The computations were performed with a 3D-Navier-Stokes code utilizing an unstructured solution adaptive grid methodology. The code uses a low Reynolds number k-epsilon model for prescribing the Reynolds stresses. The results show that there is a significant interaction between the coolant flow and the secondary flow near the hub and the tip of the turbine blade. It was observed that, by blowing on the pressure side of the blade some of the cooling air was transported through the tip gap of the blade to the suction side of the blade where the coolant flow interacts with the secondary flow field.en
dc.language.isoende
dc.rightsinfo:eu-repo/semantics/openAccessde
dc.subject.classificationTemperaturverteilung , Rotorblattde
dc.subject.ddc620de
dc.titleComputations of a film cooled turbine rotor blade with non-uniform inlet temperature distribution using a three-dimensional viscous procedureen
dc.typeconferenceObjectde
ubs.fakultaetFakultätsübergreifend / Sonstige Einrichtungde
ubs.institutSonstige Einrichtungde
ubs.opusid7047de
ubs.publikation.sourceInternational Gas Turbine and Aeroengine Congress and Exposition : The Hague, Netherlands, June 13-16, 1994. New York : ASME, 1994 (ASME Paper 94-GT-015), S. 1-9de
ubs.publikation.typKonferenzbeitragde
Enthalten in den Sammlungen:15 Fakultätsübergreifend / Sonstige Einrichtung

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