Prediction of transonic flutter in oscillating cascades
A numerical simulation method of coupled CFD-CSD analysis in turbomachinery biddings, focusing on the influence of Interblade Phase Angle (IBPA) on aeroelastic stability, was developed. The node displacements of structural model, transferring to fluid interface nodes with finite element interpolation algorithm, are obtained on the basis of Computational Structural Dynamics (CSD). As for Computational Fluid Dynamics (CFD), Finite Volume Method (FVM) is used to solve Reynolds averaged Navier-Stokes (RANS) equations with k — ε turbulence models for closure. For NASA Rotor 67, the aerodynamic work done per oscillating cycle and the corresponding aerodynamic modal damping ratios at the first three modes of rotating blade has been computed to investigate the influence of mode shape on flutter. And the effects of IBPA on flutter have also been investigated by the validated numerical method. The aerodynamic modal damping ratios form the coupled CFD-CSD analysis is feasible to preliminarily predict blades aeroelastic stability, which shows that mode shape and IBPA are the key contributors to flutter.
turbomachinery hlading flutter interblade phas angle
Zhang Xiaowei Wang Yanrong
School of Jet Propulsion Beihang University Beijing, China
国际会议
The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)
南京
英文
196-200
2010-09-13（万方平台首次上网日期，不代表论文的发表时间）