Vibration analysis of composite airfoil blade using orthotropic thin shell bending theory

Sinha, Sunil K.; Zylka, Richard P.

doi:10.1016/j.ijmecsci.2016.12.012

Cited by 50 publications

(8 citation statements)

References 31 publications

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“…The rotation of the blade about the turbine axial direction produces a significant amount of membrane stresses, which are essentially acting in the radial direction (the spanwise and chordwise directions of the blade). The component of centrifugal force along the spanwise direction σ cs and the chordwise direction σ cc can be written as [10,14]…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

“…Sun et al [13] developed a novel dynamic model for pretwisted rotating compressor blades by using the general shell theory and studied the eigenfrequencies and damping properties of the pretwisted rotating blade. Sinha and Zylka [14] derived the governing partial differential equation of motion based on the thin shell theory and formulated the free vibration of a turbomachinery cantilevered airfoil by considering it as an anisotropic shell in a centrifugal force field. Kielb et al [15] gave the complete theoretical and experimental results of a joint research study on the vibration characteristics of pretwisted cantilever plates.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Free Vibration Analysis of Rotating Pretwisted Functionally Graded Sandwich Blades

Liu

Yang

Zhang

et al. 2018

International Journal of Aerospace Engineering

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A new structural dynamic model for the free vibration characteristic analysis of rotating pretwisted functionally graded (FG) sandwich blades is developed. The sandwich blade is made up of two functionally graded skins and a homogeneous material core. The thick shell theory is applied to derive the basic equations of motion of the rotating FG sandwich blade by considering the effects of centrifugal and Coriolis forces. The mode shapes are expanded in terms of two-dimensional algebraic polynomials in the Rayleigh–Ritz method, and the static and dynamic natural frequencies of the blade are obtained. The convergence analysis is studied, and the accuracy of the proposed model is verified by comparing with the literature results and ANSYS data. The effects of frequency parameters such as the twist angle, the thickness ratio, the aspect ratio, the layer thickness ratio, the scalar parameter of volume fraction, the stagger angle, and the rotation velocity on the vibration characteristics for pretwist FG sandwich blade are investigated in detail. In addition, the phenomena of frequency locus veering and mode shape exchanging occur in the static and dynamic states. Frequency locus veering is essentially caused by the coupling between different modes.

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Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Free Vibration Analysis of Rotating Pretwisted Functionally Graded Sandwich Blades

Liu

Yang

Zhang

et al. 2018

International Journal of Aerospace Engineering

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“…where σ 1 and σ 2 are two detuning parameters. Substituting (26) and (27) into (25a) and (25b), we obtain the following equation…”

Section: Perturbation Analysismentioning

confidence: 99%

“…Sun et al [25] applied the general shell theory to investigate the influence of parameters on natural frequency and damping characteristics of the shell model blade. Sinha and Zylka [26] simplified the rotating pretwisted turbomachinery cantilevered airfoil as an anisotropic shell and derived the free vibration equations of motion for the transverse deflection of the shell including the warping effect. Volker and Joachim [27] analyzed the aeroelastic phenomena of twenty compressor blades simplified as the spring-damper models mounted on the hub.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Dynamics of the High-Speed Rotating Plate

Yao

Zhang

2018

International Journal of Aerospace Engineering

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High speed rotating blades are crucial components of modern large aircraft engines. The rotating blades under working condition frequently suffer from the aerodynamic, elastic and inertia loads, which may lead to large amplitude nonlinear oscillations. This paper investigates nonlinear dynamic responses of the blade with varying rotating speed in supersonic airflow. The blade is simplified as a pre-twist and presetting cantilever composite plate. Warping effect of the rectangular cross-section of the plate is considered. Based on the first-order shear deformation theory and von-Karman nonlinear geometric relationship, nonlinear partial differential dynamic equations of motion for the plate are derived by using Hamilton’s principle. Galerkin approach is applied to discretize the partial differential governing equations of motion to ordinary differential equations. Asymptotic perturbation method is exploited to derive four-degree-of-freedom averaged equation for the case of 1 : 3 internal resonance-1/2 sub-harmonic resonance. Based on the averaged equation, numerical simulation is used to analyze the influence of the perturbation rotating speed on nonlinear dynamic responses of the blade. Bifurcation diagram, phase portraits, waveforms and power spectrum prove that periodic motion and chaotic motion exist in nonlinear vibration of the rotating cantilever composite plate.

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“…The development of new materials-such as composite materials-has paved the way for significant mass reduction in aerospace structural components [1]. The use of such materials is indeed increasingly common for aircraft structures and even aircraft engines as they are typically found in the fan stage [7,8], acoustic lining panels [9,10,11] as well as various components of the nacelle [12,13]. However, the use of composite materials within the hot sections of an aircraft engine remains a challenge for engineers due to extreme thermal conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

Nyssen

Tableau

Lavazec

et al. 2020

Journal of Sound and Vibration

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This work focuses on the experimental and numerical characterization of stress levels within a shroud segment made of ceramic matrix composite (CMC) material undergoing repeated blade contacts. The dedicated experimental setup consists in a rotating disk with three notched mock blades that impact the shroud segment as they rotate. The underplatform on which the shroud is fixed progressively gets closer to the blades, so that the abradable layer deposited onto the shroud is progressively worn out from a blade revolution to another. Four sensors, located under the shroud segment, are used to record forces during the experiments. Different blade/shroud relative positions are tested, in such a way that impacts may occur at distinct locations. In addition to the experimental tests, a numerical model is built based on both reduced order models of the blade and the shroud segment, in order to numerically predict the forces at the four sensors. This numerical model is first calibrated based on a single reference test case to retrieve the same force magnitude at each sensor. Then, the other tests are simulated using the calibrated model. Predicted contact forces are in good agreement with experimental data, which validates the numerical model. Finally, simulations are carried out considering engine-like conditions, which could not be reproduced using the experimental test bench. The influence of several parameters (radial velocity, impact location, number of blades in contact and angular speed) is analyzed in detail.

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Vibration analysis of composite airfoil blade using orthotropic thin shell bending theory

Cited by 50 publications

References 31 publications

Free Vibration Analysis of Rotating Pretwisted Functionally Graded Sandwich Blades

Free Vibration Analysis of Rotating Pretwisted Functionally Graded Sandwich Blades

Nonlinear Dynamics of the High-Speed Rotating Plate

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

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