Flapwise bending vibration analysis of functionally graded rotating double-tapered beams
- N. V. Ramesh Maganti^{1}Email author and
- Mohan Rao Nalluri^{2}
DOI: 10.1186/s40712-015-0040-0
© Maganti and Nalluri. 2015
Received: 24 March 2015
Accepted: 29 June 2015
Published: 14 August 2015
Abstract
Background
During the past decade, many researchers have focused on the vibration characteristics of stationary and rotating functionally graded beams employing various methods of analysis. Hitherto, the studies have been mainly confined to uniform beams. Hence, the present study is aimed at studying the free vibration characteristics of functionally graded double-tapered rotating cantilever beam with symmetric cross section.
Material and Method
This paper presents a method which considers the deformation variables to determine flapwise bending vibrations of rotating functionally graded doubletapered beam attached to a rigid hub. The tapered beam is characterized by continuously variable Young’s modulus along the thickness direction according to a power law. The equations of motions are derived using hybrid deformation variables employing Lagrange’s approach. Rayleigh-Ritz method is used to evaluate the frequencies of the beam.
Results
The effect of several parameters such as material composition gradient, taper ratios, hub radius ratio and rotational speed on flapwise bending natural frequencies of tapered beams are investigated.
Conclusions
Variation in taper ratios affects the frequency parameters of the beam. The frequency parameters are observed to increase with an increase in hub radius. The power law index has negligible influence on the trend of flapwise bending natural frequencies with an increase in angular speed for different taper ratios.
Keywords
Functionally graded beam Rotating beam Rayleigh-Ritz method Flapwise vibration Double-tapered beamBackground
Generally, to increase the strength as well as stability of the structure and to reduce the weight, tapered beams have practical importance at the design stage of structures, such as the helicopter blades, rotating machinery, wind turbine blades, etc. The design as well as analysis and estimation of dynamic characteristics of these structures is very difficult. Centrifugal inertia force due to rotation is one of the critical factors in evaluating the dynamic characteristics of the rotating structures. Many researchers have investigated the dynamic characteristics of the homogeneous rotating beams in the past. Tsai et al. (2011) investigated the free vibrations for inclined Euler beam rotating at constant angular speed using the co-rotational finite element method combined with floating frame method. In this work, the equations of motion were derived in terms of an inertial global coordinate system using d’Alembert principle and principle of virtual work. A method based on the power series solution was proposed by Huang et al. (2010) for a slender beam rotating at high angular velocity, in which the beam was divided into equal segments for estimating flapwise vibration and coupled lagwise and axial vibration. New shape functions that include the rotating speed, element position, and centrifugal stiffening effect were considered to derive new finite element to evaluate free vibrations of beams rotating at high speeds by Gunda et al. (2009). Using p-version finite element method, the vibration characteristics of a rotating beam were obtained by Cheng et al. (2011). Fracture mechanics and Lagrange equation were used to obtain crack element stiffness matrix and p-version finite element model respectively in the analysis. The vibrations and reliability of rotating beams were studied considering the random properties under random excitations by Hosseini and Khadem (2007). Finite element method and space state analysis were applied to obtain the equations of motion. Free vibrations of tapered rotating beam in elastic and post elastic areas were evaluated using variational principles to derive the equations of motions in the works of Das et al. (2009). Assuming the centrifugal force as constant, the differential equation of motion of rotating beam was reduced as stiff string and natural frequencies of uniform and tapered beams were evaluated by Ganesh and Ganguli (2013) using Rayleigh-Ritz method. A new finite element was developed by Babu Gunda and Ganguli (2008) satisfying the governing equation of Euler-Bernoulli rotating beams to study the static and dynamic behavior of rotating beam. Lin et al. (2006) evaluated bending-bending vibrations of rotating damped beam with pre-twist and an elastically restrained root and their effects on the complex frequencies of rotating beams were observed. Banerjee and Jackson (2013) studied on free vibration characteristics of a rotating tapered Rayleigh beam considering centrifugal stiffening, outboard force, arbitrary hub radius, and rotary inertia.
Smooth and continuous variation in material properties in one or more directions in case of structures like beams plates and shells, which are made from functionally graded materials (FGMs), exhibits several advantages over homogeneous and laminated composite materials. During the past one decade, many researchers have turned their interest to study the vibration and dynamic characteristics of FGM structures. Sankar (2001) developed a solution for a functionally graded beam subjected to transverse loads, whose Young’s modulus was assumed to vary in thickness direction, and found that the stress concentration depends on the distribution of constituent material of the beam. Based on two-dimensional theory of elasticity, Ying et al. (2008) proposed an exact solution for free vibrations of functionally graded beams resting on elastic foundation wherein material properties were assumed to vary in thickness direction as per exponential law. Higher order shear deformation theory was implemented by Kadoli et al. (2008) to study the behavior of the FG beam with variation of material composition based on power law under uniformly distributed load with different end conditions. Differential equation and its solution for deflection of FGM beams resting on elastic foundation using second-order theory were obtained by Murin et al. (2013) and used in free vibration analysis of the beams. Considering the fourth-order differential equation of the second-order beam theory, modal analysis was carried out for beams by Aminbaghai et al. (2012). Using the first-order shear deformation theory, dynamic stiffness matrix was derived by Ziane et al. (2013) to evaluate the free vibrations of functionally graded box beam.
The above studies chiefly focused on the evaluation of dynamic characteristics of homogeneous stationary and rotating uniforms and FGM beams that are stationary. For the design and analysis of tapered rotating structures like wind turbine blades, helicopter blades, rotating machinery, etc., vibration characteristics are vital parameters. The knowledge on these characteristics play a very important role in design stage for studying the dynamic behavior and to avoid structural resonance. The flapwise and chordwise dynamic behavior of the beam depends on the nature of the transverse loads, geometry of the component, and the boundary conditions. Hitherto, the studies have been mainly confined to uniform beams. Hence, the present study is aimed at studying the free vibration characteristics of double-tapered rotating cantilever beam with symmetric cross section. The beam material considered is FGM and the variables considered are taper ratio, composition variation of material as per power law index, hub radius ratio, and rotational speed. The results so obtained are compared with those reported in the earlier works based on different approaches.
Material and Method
Functionally graded beam
where P _{(z)} represents an effective material property (i.e., density, P _{(z)}, or Young’s modulus, E _{(z)}) and P _{(m)} and P _{(c)} are metallic and ceramic properties, respectively.
The volume fraction exponent or power law index, n, is a variable whose value is greater than or equal to zero and the variation in properties of the beam depends on its magnitude. Structure is constructed with functionally graded material with ceramic rich at top and bottom surfaces (at z = h/2 and −h/2) with protecting metallic core (at z = 0).
Equations of motion
- 1.
There is a smooth and continuous variation in properties along thickness direction.
- 2.
The neutral and centroidal axes in the cross section of the rotating beam coincide so that effects due to eccentricity and torsion can be negligible.
- 3.
Cross section of the beam varies uniformly along its length with the uniform taper.
- 4.
Shear and rotary inertia effects of the beam are neglected due to slender shape of the beam.
Figure 1 shows the deformation of the neutral axis of a beam fixed to a rigid hub rotating about the axis z. The tapered beam is attached to a rigid hub which rotates with constant angular speed and no external force acts on the beam. The beam rotates at an angular speed of Ω (t) about the z-axis. In the present work, a hybrid set of Cartesian variable w and a non-Cartesian variable s is approximated by spatial functions and corresponding coordinates are employed to derive the equations of motion. The position of a generic point on the neutral axis of the double-tapered beam before deformation located at P _{0} changes to P after deformation and its elastic deformation is denoted as \( \widehat{d} \) that has two components in two-dimensional space.
Approximation of deformation variables
In the above equations, ϕ _{1j } and ϕ _{3j } are the assumed modal functions (test functions) for s and w, respectively. Any compact set of functions which satisfies the essential boundary conditions of the cantilever beam can be used as the test functions. The q _{ ij }s are the generalized coordinates and μ _{1} and μ _{3} are the number of assumed modes used for s and w, respectively. The total number of modes, μ, is equal to the sum of individual modes, i.e., μ = μ _{1} + μ _{3} .
where a symbol with a prime (′) represents the partial derivative of the symbol with respect to the integral domain variable.
Strain energy of the system
where I _{ y(x)} is the second moment of area of the tapered beam.
Kinetic energy of the system
In which, A _{(x)} is the area of cross section of the tapered beam, P _{(z)} is the mass density, and L is the length of the beam.
Equation of motion
where a symbol with double prime (″) represents the second derivative of the symbol with respect to the integral domain variable.
Dimensionless transformation
where τ, δ, and γ refer to dimensionless time, hub radius ratio, and dimensionless angular speed, respectively.
Analysis of flapwise bending natural frequencies
Equation 22 governs the flapwise bending vibration of the double-tapered rotating beam which is not coupled with Eq. 21. With the assumption that the first stretching natural frequency of an Euler beam far separated from the first natural frequency, Eq. 21 is ignored in present analysis. Equation 22 involves the parameters L, Ω, x, E, and P , which are the properties of the beam.
where ψ _{ ai } is a function of ξ that has the same functional value of x.
Results and discussion
The procedure presented above for free vibration analysis of a double-tapered beam is demonstrated through numerical examples.
Comparison of the non-dimensional lowest three flapwise bending natural frequencies of a homogenous stationary beam with different taper ratios (δ = 0)
τ _{ h } | τ _{ b } | 0.2 | 0.4 | 0.6 | 0.8 |
---|---|---|---|---|---|
0.0 | |||||
(a) Fundamental frequency | |||||
0.0 | 3.15601 | 3.76285 | 4.09697 | 4.58531 | 5.39758 |
3.51602^{a} | 3.76286^{a} | 4.09698^{a} | 4.58531^{a} | 5.39759^{a} | |
0.2 | 3.60827 | 3.85511 | 4.18932 | 4.67815 | 5.49265 |
3.60828^{a} | 3.85512^{a} | 4.18932^{a} | 4.67816^{a} | 5.49266^{a} | |
0.4 | 3.73707 | 3.98419 | 4.31877 | 4.80842 | 5.62551 |
3.73708^{a} | 3.98419^{a} | 4.31878^{a} | 4.80842^{a} | 5.62552^{a} | |
0.6 | 3.93427 | 4.18234 | 4.51799 | 5.00903 | 5.82882 |
3.93428^{a} | 4.18235^{a} | 4.51799^{a} | 5.00903^{a} | 5.82882^{a} | |
0.8 | 4.29250 | 4.54369 | 4.88244 | 5.37615 | 6.19641 |
4.29249^{a} | 4.54368^{a} | 4.88244^{a} | 5.37614^{a} | 6.19639^{a} | |
(b) Second natural frequency | |||||
0.0 | 22.0344 | 22.5018 | 23.1186 | 24.0210 | 25.6558 |
22.0345^{a} | 22.5018^{a} | 23.1186^{a} | 24.0211^{a} | 25.6558^{a} | |
0.2 | 20.6210 | 21.0567 | 21.6327 | 22.4774 | 24.0153 |
20.6210^{a} | 21.0567^{a} | 21.6327^{a} | 22.4774^{a} | 24.0153^{a} | |
0.4 | 19.1138 | 19.5166 | 20.0500 | 20.8343 | 22.2710 |
19.1138^{a} | 19.5166^{a} | 38.4920^{a,b} | 20.8343^{a} | 22.2710^{a} | |
0.6 | 17.4879 | 17.8557 | 18.3441 | 19.0649 | 20.3953 |
17.4879^{a} | 17.8557^{a} | 18.3441^{a} | 19.0649^{a} | 20.3952^{a} | |
0.8 | 15.7473 | 16.0731 | 16.5132 | 17.1668 | 18.3871 |
15.7427^{a} | 16.0725^{a} | 16.5123^{a} | 17.1657^{a} | 18.3855^{a} | |
(c) Third natural frequency | |||||
0.0 | 61.6972 | 62.1525 | 62.7763 | 63.7515 | 65.7470 |
61.6972^{a} | 62.1525^{a} | 62.7763^{a} | 63.7515^{a} | 65.7470^{a} | |
0.2 | 56.1923 | 56.6304 | 57.2258 | 58.1467 | 60.0096 |
56.1923^{a} | 56.6303^{a} | 57.2257^{a} | 58.1466^{a} | 60.0094^{a} | |
0.4 | 50.3537 | 50.7715 | 51.3348 | 52.1965 | 53.9177 |
50.3537^{a} | 50.7714^{a} | 51.3346^{a} | 52.1963^{a} | 53.9173^{a} | |
0.6 | 44.0252 | 44.4180 | 44.9437 | 45.7391 | 47.3066 |
44.0248^{a} | 44.4175^{a} | 44.9432^{a} | 45.7384^{a} | 47.3051^{a} | |
0.8 | 36.8955 | 37.2558 | 37.7358 | 38.4555 | 39.8568 |
36.8846^{a} | 37.2439^{a} | 37.7223^{a} | 38.4392^{a} | 39.8336^{a} |
Variation of the first three non-dimensional natural frequencies, with respect to the rotational speed parameter, γ, and the hub radius parameter, δ (τ_{b} = 0, τ_{h} = 0.5)
δ | γ | First frequency | Second frequency | Third frequency | |||
---|---|---|---|---|---|---|---|
Present approach | Ref. (Ozgumus and Kaya 2006) | Present approach | Ref. (Ozgumus and Kaya 2006) | Present approach | Ref. (Ozgumus and Kaya 2006) | ||
0.0 | 1 | 4.017 | 3.986 | 18.501 | 18.474 | 47.448 | 47.417 |
2 | 4.547 | 4.436 | 19.045 | 18.936 | 47.995 | 47.871 | |
3 | 5.308 | 5.092 | 19.917 | 19.683 | 48.891 | 48.619 | |
4 | 6.211 | 5.878 | 21.077 | 20.685 | 50.117 | 49.645 | |
2.0 | 1 | 4.482 | 4.386 | 18.974 | 18.879 | 47.939 | 47.830 |
2 | 6.033 | 5.742 | 20.819 | 20.473 | 49.902 | 49.486 | |
3 | 7.955 | 7.452 | 23.562 | 22.879 | 52.995 | 52.120 | |
4 | 10.027 | 9.310 | 26.918 | 25.866 | 57.013 | 55.581 | |
0.5 | 1 | 4.138 | 4.090 | 18.621 | 18.576 | 47.571 | 47.521 |
2 | 4.961 | 4.797 | 19.504 | 19.332 | 48.480 | 48.281 | |
3 | 6.082 | 5.777 | 20.892 | 20.531 | 49.953 | 49.520 | |
4 | 7.359 | 6.905 | 22.689 | 22.099 | 51.940 | 51.201 | |
1.0 | 1 | 4.256 | 4.191 | 18.739 | 18.677 | 47.694 | 47.624 |
2 | 5.343 | 5.132 | 19.953 | 19.720 | 48.959 | 48.686 | |
3 | 6.766 | 6.386 | 21.821 | 21.343 | 50.990 | 50.403 | |
4 | 8.346 | 7.793 | 24.187 | 23.425 | 53.692 | 52.706 |
From the data, it has been observed that there is nearly one-to-one correspondence between the results obtained from the current approach and those reported based on the differential transform method.
In view of this observation, it is opined that the current approach is in order and has been adopted for further analysis in this study.
Properties of metallic (steel) and ceramic (alumina) materials
Properties of materials | Steel | Alumina (Al_{2}O_{3}) |
---|---|---|
Young’s modulus E (GPa) | 214.00 | 390.00 |
Material density ρ (kg/m^{3}) | 7800.00 | 3200.00 |
The frequencies are evaluated with ten assumed modes to obtain the converged bending natural frequencies. As the frequencies obtained with number of modes greater than ten did not show any significant improvement in the results, the number of assumed modes is restricted to ten only.
For all the values of power law index, all frequencies are observed to increase with the increase in height taper ratio and the first flapwise frequency is observed to increase while a decreasing trend has been observed in case of higher frequencies with an increase in width taper ratio. It is also observed that, at higher values of power law index, the variation of flapwise bending natural frequencies with a variation in width and height taper ratios tends to reduce.
It has been observed that for different values of taper ratios and power law indices, the fundamental frequencies are diverging with the increase in angular speed and all higher order frequencies are observed to be converging. However, at a given speed, the frequencies decrease with an increase in power law index.
It is also observed that the influence of taper ratio on fundamental flapwise bending natural frequency is increasing with the increase in angular speed and the influence is less on higher modes of vibration. The power law index has negligible influence on the trend of flapwise bending natural frequencies with the increase in angular speed for different taper ratios which is evident from similarity of variation pattern for solid (n = 0) and that for dashed (n = 2.0) and dotted (n = 4.0) lines for all modes of vibration. These trends should be expected that the tapered beams under consideration would behave differently, as the stiffness at the root and load variation along the length of the beam depend on the taper ratio.
Conclusions
The free flapwise bending vibrations of a rotating tapered beam are investigated in this work. The equations of motions are derived using hybrid deformation variables employing Lagrange’s approach. Rayleigh-Ritz method is used to evaluate the frequencies of the beam. Linear tapering in breadth and depth directions is considered for the analysis. Variation in taper ratios affects the frequency parameters of the beam. The frequency parameters are observed to increase with the increase in hub radius parameter. The power law index has negligible influence on the trend of flapwise bending natural frequencies with the increase in angular speed for different taper ratios.
Declarations
Open AccessThis article is distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license, and indicate if changes were made.
Authors’ Affiliations
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