Aeroelastic instability studies of rotating tapered composite sandwich blades with magnetorheological elastomeric core

Abstract

The vibration minimization using a certain class of absorption materials is a goal in many recent dynamic systems. Magnetorheological elastomer is one kind of such material, which exhibits variable rheological properties like viscosity due to the magnetic field's influence. Aeroelastic analysis of such rotating structures is crucial in wind turbines and turbomachinery. In this article, aeroelastic stability studies of rotating non- uniform composite sandwich beam embedded with magnetorheological elastomer in supersonic flow are presented. Magnetorheological core layer is sandwiched between the composite face layers in this beam. For composite layers, the problem is formulated using beam theory, the magnetic field- dependent complex modulus is used to determine the magnetorheological core layer's constitutive behavior and aerodynamic pressure is modeled with piston theory. Lagrange’s equation is applied to obtain the equations of motion for the sandwich beam and solved by the finite element technique. The published values of the natural frequencies are compared and the influence of rotational speed, aerodynamic pressure, setting angle, intensity of magnetic field, hub radius, taper ratio parameters, and ply orientation on the fundamental frequency are studied. The results reveal that by changing specific composite beam parameters, the flutter boundaries of the rotating beam may be expanded.