A Non-linear Integrated Aeroelasticity Method for the Prediction of Turbine Forced Response with Friction Dampers
2001 (English)In: International journal of mechanical sciences, ISSN 0020-7403, Vol. 43, no 12, 2715-2736 p.Article in journal (Refereed) Published
An integrated aeroelasticity model was described for turbine blade forced response predictions. An iterative procedure was developed to determine the resonance shift under the effects of both unsteady dynamic loading and non-linear friction dampers. The forced response computations were conducted using a multi-bladerow approach to avoid errors associated with linking single bladerow computations since the spacing between the bladerows was relatively small. For the 40 engine-order resonances in torsion and blending modes, frequency shifts of 3.2% and 20.0% were predicted. The predicted frequency shifts and the dynamic behavior of the friction dampers were found to be within the measured range.
Place, publisher, year, edition, pages
2001. Vol. 43, no 12, 2715-2736 p.
Nonlinear Approach; Turbomachinery; Grids
IdentifiersURN: urn:nbn:se:kth:diva-5978DOI: 10.1016/S0020-7403(01)00074-1ISI: 000172633800001OAI: oai:DiVA.org:kth-5978DiVA: diva2:10532
QC 201008242006-06-072006-06-072010-12-06Bibliographically approved