Part-Speed Flutter Analysis of a Wide-Chord Fan Blade

摘要: Experimental and theoretical results are reported in this paper for a flutter research rig with 26 wide-chord fan blades. The structural model was based on 3D finite element eigensolution while two different unsteady aerodynamic codes were used the fluid. first one is thin-layer Reynolds-averaged Navier-Stokes solver using structured meshes it specified blade motion interblade phase angle. second code an implicit upwind that uses unstructured of tetrahedra elements. An inviscid flow representation, together viscous loss model, whole annulus calculations flexible approach integrated aeroelasticity analysis sense fluid equations solved coupled fashion by exchanging data at each step time integration. Flutter predictions attempted 75%, 80% 85% speeds least stable vibration modes found to lie within 0–3 nodal diameter range, agreement experimental observations. predicted variation margins respect speed exhibit fair correlation available data. A detailed investigation blade’s surface pressure fluctuations revealed linear perturbation trend from mean solution highlighted importance getting correct shock position steady calculations. Also, provided support mechanism which discussed some detail.