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Research Papers: Gas Turbines: Structures and Dynamics

Variable Kinematic One-Dimensional Finite Elements for the Analysis of Rotors Made of Composite Materials

[+] Author and Article Information
E. Carrera

Professor
Department of Mechanical
and Aerospace Engineering,
Politecnico di Torino,
Corso Duca degli Abruzzi 24,
Torino 10129, Italy;
School of Aerospace, Mechanical
and Manufacturing Engineering,
RMIT University,
Melbourne, Australia
e-mail: erasmo.carrera@polito.it

M. Filippi

Department of Mechanical
and Aerospace Engineering,
Politecnico di Torino,
Corso Duca degli Abruzzi 24,
Torino 10129, Italy
e-mail: matteo.filippi@polito.it

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 18, 2014; final manuscript received February 24, 2014; published online April 18, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(9), 092501 (Apr 18, 2014) (11 pages) Paper No: GTP-14-1109; doi: 10.1115/1.4027192 History: Received February 18, 2014; Revised February 24, 2014

This paper deals with the dynamic response of rotors made of anisotropic, laminated composite materials. It is a sequel to the authors’ previous work, which was devoted to the rotordynamics of metallic structures. The used variable kinematic one-dimensional models describe any cross-sectional deformation of the rotor and go beyond the plane strain assumptions of classical Euler–Bernoulli and Timoskenko beam theories. Refined theories are obtained by applying the Carrera unified formulation, which is extended here to the rotordynamics of multilayered composites. The displacement variables over the rotor cross section x-z plane are approximated by x,z polynomials of any order N. Thin-walled cylindrical shafts and boxes are analyzed. These structures are made of unidirectional layers, whose fiber orientation can vary with respect to the rotor–axis as well as in the x-z plane. Several analyses have been carried out to determine the vibrational response as a function of the rotating speed. Classical beam theories are obtained as particular cases and results available in the literature, including shell results, are used to assess the presented theory. The proposed refined models are very effective in investigating the dynamic behavior of laminated composite rotors.

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References

Figures

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Fig. 1

Physical and material reference systems

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Fig. 7

Dependency of frequency and damping ratios upon the speed parameter for a cantilever box beam (R = 0.5): (a) lines θ = 0, bold lines θ = 15, (b) frequency ratios TE6, and (c) damping ratios TE6

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Fig. 6

Dependency of frequency and damping ratios upon the speed parameter for a cantilever box beam (R = 1 and case II): (a) EBBT, FSDT and (b) TE3, TE6

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Fig. 5

Dependency of frequency ratio and damping upon the speed parameter for a cantilever box beam (R = 1 and case I): (a) EBBT, FSDT and (b) TE3, TE6

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Fig. 4

Dependency of frequency ratio upon the speed parameter for various values of ply angles (R = 1): solid line TE2, dashed line TE6

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Fig. 3

Dependency of frequency ratios upon the speed parameter for the cantilever box beam (R = 1): (a) θ = 0 and (b) θ = 90

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Fig. 2

Sketch of the box beam

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