Effect of scaling of blade row sectors on the prediction of aerodynamic forcing in a highly-loaded transonic compressor stage
2009 (English)In: PROCEEDINGS OF THE ASME TURBO EXPO 2009, VOL 6, PTS A AND B, 2009, 535-546 p.Conference paper (Refereed)
An investigation of the sensitivity of a geometrical scaling technique on the blade forcing prediction and mode excitability has been performed. A stage of a transonic compressor is employed as test object. A scaling ratio is defined which indicates the amount of scaling from the original geometry. Different scaling ratios are selected and 3D Navier Stokes unsteady calculations completed for each scaled configuration. A full annulus calculation (non-scaled) is performed serving as reference. The quantity of interest is the generalized force, which gives a direct indication of the mode excitability. In order to capture both up- and downstream excitation effects the mode excitability has been assessed on both rotor and stator blades. The results show that first harmonic excitation can be predicted well for both up- and downstream excitation using moderate amount of scaling. On the other hand, the predictions of second harmonic quantities do show a higher sensitivity to scaling for the investigated test case.
Place, publisher, year, edition, pages
2009. 535-546 p.
aeromechanical design, unsteady forces, CFD, turbomachinery, blade row interaction, scaling, aerodynamic forcing, fluid structure interaction
IdentifiersURN: urn:nbn:se:kth:diva-11958DOI: 10.1115/GT2009-59601ISI: 000277070700055ScopusID: 2-s2.0-77953225029ISBN: 978-0-7918-4887-6OAI: oai:DiVA.org:kth-11958DiVA: diva2:291109
54th ASME Turbo Expo 2009, Orlando, FL, JUN 08-12, 2009
QC 201102222010-02-082010-01-292011-03-24Bibliographically approved