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Stability analysis of flexible wind turbine blades using finite element method
TLDR
In this paper, the static vibration and flutter analysis of a straight elastic axis blade was performed based on a finite element method solution, and the total potential energy functional was formulated according to linear beam theory.Abstract:
Static vibration and flutter analysis of a straight elastic axis blade was performed based on a finite element method solution. The total potential energy functional was formulated according to linear beam theory. The inertia and aerodynamic loads were formulated according to the blade absolute acceleration and absolute velocity vectors. In vibration analysis, the direction of motion of the blade during the first out-of-lane and first in-plane modes was examined; numerical results involve NASA/DOE Mod-0, McCauley propeller, north wind turbine and flat plate behavior. In flutter analysis, comparison cases were examined involving several references. Vibration analysis of a nonstraight elastic axis blade based on a finite element method solution was performed in a similar manner with the straight elastic axis blade, since it was recognized that a curved blade can be approximated by an assembly of a sufficient number of straight blade elements at different inclinations with respect to common system of axes. Numerical results involve comparison between the behavior of a straight and a curved cantilever beam during the lowest two in-plane and out-of-plane modes.read more
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Stability of nonuniform rotor blades in hover using a mixed
TL;DR: In this paper, a mixed formulation for calculating static equilibrium and stability eigenvalues of non-uniform rotor blades in hover is presented, where the static equilibrium equations are nonlinear and are solved by an accurate and efficient collocation method.
References
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Differential equations of motion for combined flapwise bending, chordwise bending, and torsion of twisted nonuniform rotor blades
John C. Houbolt,George W Brooks +1 more
TL;DR: In this article, the differential equations of motion for the lateral and torsional deformations of twisted rotating beams are developed for application to helicopter rotor and propeller blades, and the generality is such that previous theories involving various simplifications are contained as subcases to the theory presented in this paper.
Stability of elastic bending and torsion of uniform cantilever rotor blades in hover with variable structural coupling
TL;DR: In this paper, the stability of elastic flap bending, lead-lag bending, and torsion of uniform, untwisted, cantilever rotor blades without chordwise offsets between the elastic, mass, tension, and areodynamic center axes is investigated for the hovering flight condition.
Journal ArticleDOI
Dynamic stability of a rotor blade using finite element analysis
N. T. Sivaneri,Inderjit Chopra +1 more
TL;DR: In this article, the aeroelastic stability of a helicopter rotor blade in hover is examined using a finite element formulation based on the principle of virtual work, where the rotor blade is discretized into beam elements, each with ten modal degrees of freedom.
Journal Article
Aeroelastic stability and response of horizontal axis wind turbine blades
TL;DR: In this article, the coupled flap-lag-torsion equations of motion of an isolated horizontal axis wind turbine blade were formulated and a quasi-steady blade-element strip theory was applied to derive the aerodynamic operator which includes boundary layer type gradient winds.
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Aeroelastic stability and response of horizontal axis wind turbine blades
TL;DR: In this article, coupled flap-lag-torsion equations of motion of an isolated horizontal axis wind turbine (HAWT) blade have been formulated and a new and convenient method of generating an appropriate time-dependent equilibrium position, required for the stability analysis, has been implemented and found to be computationally efficient.