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Investigation of unsteady aerodynamic blade excitation mechanisms in a transonic turbine stage - Part I: Phenomenological identification and classification
KTH, Superseded Departments, Energy Technology.
KTH, Superseded Departments, Energy Technology.
2002 (English)In: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 124, no 3, 410-418 p.Article in journal (Refereed) Published
Abstract [en]

Based on the results of time-dependent 3-D viscous computations the aerodynamic mechanisms that cause the unsteady pressure fluctuations on the vane and rotor blade surface of a high-pressure transonic turbine are identified and separately classified in a phenomenological manner. In order to be able to describe separately the influence of wake, potential and shock distortions on the blade surface pressure tit design operation conditions, the stator exit Mach number is increased as to enhance the shock distortions and lowered as to enhance potential anti wake distortions, In a comprehensive approach the observations from the off-design conditions are utilized to classify every major perturbation observed in the perturbation space-time maps tit design operation conditions. The spanwise variations caused by the inherent 3-D nature of the flow field and promoted by the 3-D shape of the rotor blade are addressed.

Place, publisher, year, edition, pages
2002. Vol. 124, no 3, 410-418 p.
Keyword [en]
rotor-stator interaction, flow, simulation, pressure
National Category
Energy Engineering
Identifiers
URN: urn:nbn:se:kth:diva-21743DOI: 10.1115/1.1458577ISI: 000177013500013OAI: oai:DiVA.org:kth-21743DiVA: diva2:340441
Note
QC 20100525 QC 20111129Available from: 2010-08-10 Created: 2010-08-10 Last updated: 2017-12-12Bibliographically approved

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