Investigation of unsteady aerodynamic blade excitation mechanisms in a transonic turbine stage - Part I: Phenomenological identification and classification
2002 (English)In: Journal of turbomachinery, ISSN 0889-504X, Vol. 124, no 3, 410-418 p.Article in journal (Refereed) Published
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.
rotor-stator interaction, flow, simulation, pressure
IdentifiersURN: urn:nbn:se:kth:diva-21743DOI: 10.1115/1.1458577ISI: 000177013500013OAI: oai:DiVA.org:kth-21743DiVA: diva2:340441
QC 20100525 QC 201111292010-08-102010-08-102011-11-29Bibliographically approved