Assessment of a 3D Linear Flutter Prediction Tool using Sector Cascade Test Data
2005 (English)In: Proceedings of the ASME Turbo Expo 2005, Vol 4, ASME Press, 2005, 613-623 p.Conference paper (Refereed)
An assessment and validation of a numerical prediction tool for flutter are made using new experimental data from experiments on turbine blades in a sector cascade. The 3D geometry is that of a low-pressure (LP) turbine blade with twist and a profile that changes along span in an annular sector cascade. The numerical model is a linear harmonic Euler equation solver. Rig results are obtained for the blade by oscillating I blade out of 7 in the annular sector cascade. The blade is oscillated in the rig using a mechanical type of actuator to control the mode. The mode shapes in the rig consist of torsion and bending modes around a pivot mechanism fixed inside the hub end wall. The frequencies obtained in the rig are in the range up to 219 Hz, or reduced frequency based on full chord k=0.5, which covers the range of useful reduced frequencies typically found in turbine designs. Under reference running conditions the unsteady pressure responses are found qualitatively in line with the experiment. The test case is shown to be challenging to the numerical tool in terms of effects of tip clearance as well as off-design effects. In order to improve results tip clearance modeling and inclusion of viscous terms are identified as key factors.
Place, publisher, year, edition, pages
ASME Press, 2005. 613-623 p.
Euler equations, Low-pressure (LP), Numerical prediction tool, Pressure responses
IdentifiersURN: urn:nbn:se:kth:diva-78416DOI: 10.1115/GT2005-68453ISI: 000243376700068ScopusID: 2-s2.0-27744445065ISBN: 0-7918-4727-6OAI: oai:DiVA.org:kth-78416DiVA: diva2:492455
ASME Turbo Expo 2005 - Gas Turbie Technology: Focus for the Future; Reno-Tahoe, NV; United States; 6 June 2005 through 9 June 2005
QC 201203052012-02-082012-02-082014-12-01Bibliographically approved