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Unsteady boundary layer transition on a high pressure turbine rotor balde

Tiedemann, M. und Kost, F. (1999) Unsteady boundary layer transition on a high pressure turbine rotor balde. ASME TURBO EXPO, 1999.

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Kurzfassung

This investigation is aimed at the experimental determination of the location, the extent, and the modes of the laminar-to-turbulent transition processes in the boundary layers of a high pressure turbine rotor blade. The results are based on time-resolved, qualitative wall shear stress data which was derived from surface hotfilm measurements. The tests were conducted in the "Windtunnel for Rotating Cascades" of the DLR in Göttingen. For the evaluation of the influence of passing wakes and shocks on the unsteady boundary layer transition, a test with undisturbed rotor inlet flow was conducted in addition to full stage tests. Two different transition modes led to a periodic-unsteady, multimoded transition on the suction side. In between two wakes, transition started in the bypass mode and terminated as separated-flow transition. Underneath the wakes, plain bypass transition occurred. The weak periodic boundary layer features on the pressure side indicate that this surface was not significantly affected by passing wakes or shocks. The acquired data reveals that the periodically disturbed suction side boundary layer is less susceptible to bubble bursting than the undisturbed flowfield. Thus, these blades may be subjected to higher aerodynamic loads. Accordingly, as in low pressure turbines, the unsteady effects in high pressure turbines may allow for a reduction of the number of rotor blades, with respect to the original design

Dokumentart:Konferenzbeitrag (Vortrag)
Zusätzliche Informationen: LIDO-Berichtsjahr=1999,
Titel:Unsteady boundary layer transition on a high pressure turbine rotor balde
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Tiedemann, M.NICHT SPEZIFIZIERT
Kost, F.NICHT SPEZIFIZIERT
Datum:1999
Status:veröffentlicht
Stichwörter:high pressure turbine, boundary layer transition, unsteady, hotfilm, transonic
Veranstaltungstitel:ASME TURBO EXPO, 1999
Veranstalter :ASME
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Luftfahrt
HGF - Programmthema:keine Zuordnung
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L TT - Triebwerkstechnologien
DLR - Teilgebiet (Projekt, Vorhaben):NICHT SPEZIFIZIERT
Standort: Köln-Porz , Braunschweig , Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Institut für Strömungsmechanik
Hinterlegt von: elib DLR-Beauftragter
Hinterlegt am:16 Sep 2005
Letzte Änderung:14 Jan 2010 20:31

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