Thermal effects on vibration and stability of functionally graded cylindrical shells surrounded by Pasternak elastic foundation
Info: 6796 words (27 pages) Dissertation
Published: 21st Feb 2022
Tagged: Engineering
Abstract
Vibration and stability analyses of functionally graded cylindrical shells surrounded by elastic foundation under axial and thermal loads are investigated in this paper. Using Hamilton’s principle, governing equations are derived based on firstorder shear deformation theory (FSDT) assumptions and SandersKoiter formulation. Galerkin’s method is implemented to achieve the relevant expressions for frequency parameters and critical axial/thermal loads. Emphasis is placed on the solution method to derive a more accurate heat conduction equation through the shell thickness. The following two solution methods are considered: analytical exact solution and polynomial series solution. In some cases the latter solution method that has extensive application is observed to have some significant effects on the results, especially on the stability characteristics. A comprehensive validation of the results also has been provided.
Keywords: FG cylindrical shell; Vibration and stability; Axial and thermal loads; Pasternak Elastic Foundation.
1. Introduction
The use of functionally graded materials (FGMs) in various applications has increased in recent years. The idea of FGMs was first introduced by a team of Japanese scientists in 1984 [1]. FGMs are a form of composite materials that are designed to have desired properties for specific applications. FGMs are considered as a solution for the aerospace industries where high temperature resistance and lightweight but stiff structures need to be provided. These new materials with excellent thermomechanical properties are resistant to high temperatures. Functionally graded (FG) cylindrical shells also have extensive applications in different engineering structures, such as aerospace, pressure vessels and pipes, chemical plants, etc.
Among the various researches on FGMs, one of the most interesting issues is to analyze the vibration and stability behaviors of shells. Analytical study of the shells predicts the necessary mechanical measures to avoid the expected damage to the system and ensures its safety and stability. Many studies have been reported on the vibration and stability of FG cylindrical shells (Loy et al. [2], Pradhan et al. [3], Najafizadeh and Isvandzibaei [4, 5], Matsunaga [6], Tornabene [7], Huang et al. [8], Malekzadeh and Heydarpour [9], Ebrahimi and Sepiani [10] and Naeem et al. [11]). Isvandzibaei et al. [12] investigated vibration behavior of FGM cylindrical shells including internal pressure and ring support effects based on LoveKirchhoff theory with various boundary conditions. Mechanical buckling analysis of moderately thick FG cylindrical panels subjected to axial compression for combinations of clamped and simply supported boundary conditions is considered by Golmakani et al. [13]. Hadi et al. [14] studied free vibration characteristics of FGM cylindrical shells surrounded by elastic medium under axial force, lateral pressure and different boundary conditions using wave propagation method.
Free vibration analysis of simply supported FG cylindrical shells in thermal environment based on Love’s thin shell theory was performed by Haddadpour et al. [15]. Pradyumna et al. [16] investigated free vibration and buckling behavior of singly and doubly curved FG shell panels in thermal environments. Thermal buckling loads of cylindrical shells of functionally graded materials were investigated by Shahsiah and Eslami [17]. Sheng and Wang [18] investigated the effect of thermal load on the vibration, buckling and dynamic stability of FG cylindrical shells embedded in a linear elastic medium, based on the firstorder shear deformation theory (FSDT) considering the rotary inertia and transverse shear strains. The postbuckling response of an FG cylindrical shell of finite length, embedded by a Pasternaktype elastic medium and subjected to lateral pressure in thermal condition was carried out by Shen et al. [19]. Shah et al. [20] studied vibrations of FG cylindrical shells based on Winkler and Pasternaktype elastic foundations. Stress analysis of a rotating disk made of FGMs by using finite element method (FEM) and considering the effect of thickness variation and dependency of material properties to temperature distribution is conducted by Damircheli and Azadi [21]. Bagherizadeh et al. [22, 23] studied the mechanical and thermal buckling behavior of FG cylindrical shells surrounded by Pasternak elastic foundation. Ovesy and Fazilati [24] performed parametric instability analysis of moderately thick FG cylindrical panels using finite strip methods (FSM). They used Reddytype third order shear deformation theory (HSDT) and two versions of FSM, namely semianalytical and Bspline methods, were developed. Ovesy et al. [25] used semianalytical finite strip method for analyzing the postbuckling behavior of FG rectangular plates in thermal environments where plates are under uniform, tentlike or nonlinear temperature change through the thickness. Nonlinear transient heat conduction analysis for hollow thick temperaturedependent 2DFGM cylinders subjected to transient nonuniform axisymmetric thermal loads is developed by Shojaeefard and Najibi [26].
In the aforementioned thermal studies and many others, the thermal loads may be simulated in three types: (1) uniform temperature rise; (2) linear temperature change through the thickness; (3) nonlinear temperature change through the shell thickness when the temperature distribution is governed by the steady state heat conduction equation. In the third case, many researchers assume a solution in the form of a power series, but no attention is paid to the possible drawback of this solution method. To the best of authors’ knowledge, the vibration and stability analyses of FG cylindrical shells surrounded by an elastic medium under thermomechanical loads for which the nonlinear temperature distribution through the shell thickness are obtained by different approaches, are not reported elsewhere. Thus, the latter task is fulfilled in the current paper. The material properties of the FGM including Young’s modulus, Poisson’s ratio, density, thermal expansion coefficient and thermal conductivity are assumed to be variable according to a power law function through the thickness coordinate. The Pasternak model is used to describe the reaction of the elastic foundation on the cylindrical shell. Governing equations based on the FSDT of SandersKoiter for the cylindrical shells are derived. The boundary condition is considered to be simplysupported. The governing equations are solved by using the Galerkin’s method. The results of this study are compared with the available results in the literature, wherever possible. Based on the validated results, the emphasis is partially placed on the solution method to achieve a more accurate heat conduction equation through the shell thickness. Comparing the results with exact analytical solution, it is observed that in some cases the series approach for temperature distribution through the shell thickness has a significant effect on the results, especially on the stability characteristics and it can lead to predict inaccurate results.
2. Theoretical aspects
Consider a circular cylindrical shell whose constant thickness, radius and axial length are denoted by h, R and L, respectively (see Fig. 1). The present study considers functionally graded material composed of two materials. Suppose that a typical material property P(z) is varied along the shell thickness according to the following expressions (a power law):
Pz=PoPiVo+Pi, Vo=z+0.5hhN, 0≤N≤∞, h/2≤z≤h/2 

where
Po and Pi denote the property at the outer and inner surfaces of the shell, respectively; and N expresses the volume fraction exponent. Here we assume that elastic modulus
E, mass density
ρ, Poisson’s ratio
υ, thermal expansion
α, and thermal conductivity
k vary according to Eq. (1).
Fig. 1. The FG cylindrical shell on Pasternak elastic foundation under axial and thermal loads.
Based on the first order shear deformation theory, the displacements of any arbitrary point in the shell thickness could be expressed as:
U=ux,θ,t+zψxx,θ,t ,
V=vx,θ,t+zψθx,θ,t , W=wx,θ,t 

where u, v and w are the midplane displacement components along the x, θ and z directions, respectively; and ψx and ψθ denote rotations about the θ and x axes, respectively, of corresponding point on the midplane (i.e. z = 0).
The strains associated with the displacement field (2) can be expressed as:
εxx=εx,0+zkx , εθθ=εθ,0+zkθ ,
γxθ=γxθ,0+zkxθ , γxz=γxz,0 , γθz=γθz,0 

where εi,0(i=x,θ) and γi,0(i=xθ,xz,θz) are normal and shear strains of the midplane and ki(i=x,θ,xθ) denote the midplane curvatures. Relations between midplane strains, curvatures and displacements (kinematics relations) based on the SandersKoiter FSDT are as follows [27]:
εx,0=∂u∂x , εθ,0=∂vR∂θ+wR ,
γxθ,0=∂uR∂θ+∂v∂x , γxz,0=ψx+∂w∂x , γθz,0=ψθ+∂wR∂θvR , kx=∂ψx∂x , kθ=∂ψθR∂θ , kxθ=∂ψxR∂θ+∂ψθ∂x+12R∂v∂x∂uR∂θ 

Considering the thermal effects, constitutive relations are given by:
NxxNθθNxθMxxMθθMxθ=A11 A12 0 B11 B12 0A12 A22 0 B12 B22 00 0 A66 0 0 B66B11 B12 0 D11 D12 0B12 B22 0 D12 D22 00 0 B66 0 0 D66εx,0εθ,0γxθ,0kxkθkxθNxxNθθNxθMxxMθθMxθth
QxQθ=C4400C55γxz,0γθz,0 

where Aij,Bij,Dij and Cii are the extensional, coupling, bending, and shear stiffness, respectively and are defiend as:
Aij,Bij,Dij=∫h2h2Qij1,z,z2dz , i,j=1,2,6
Cii=∫h2h2Qiidz , i=4,5 Q11=Q22=Ez1υ2z , Q12=υzEz1υ2z , Q66=Ez21+υz , Q44=Q55=KEz21+υz 

E(z) is Young’s modulus, υ(z) is Poisson’s ratio and K is the shear correction factor chosen equal to 5/6 [28] and thermal stresses and moments resultants are defined as:
NxxNθθNxθMxxMθθMxθth=∫h2h2Q11+Q12Q12+Q220Q11+Q12zQ12+Q22z0αz∆Tzdz ,
∆Tz=TzTi 

α(z)
is the thermal expansion coefficient of the FGM cylindrical shell. According to Eq. (6), it is seen that A11=A22, B11=B22, D11=D22 and C44=C55.
ΔT(z) is the temperature change relative to the stress free state, and the inner surface temperature
Ti is assumed to be the initial temperature. The thermal stress is zero at T(z)=Ti.
The temperature distribution through the thickness is obtained by solving the steadystate heat conduction equation through the thickness of the FG cylindrical shell. The equation for the temperature field through the thickness is given by [28]:
ddzk(z)dTdz=0 

where the thermal conductivity
k(z) of the FG cylindrical shell is assumed to vary according to power law. Eq. (8) is solved by imposing the boundary conditions
T(h/2)=Ti and T(h/2)=To. The solution of this equation, obtained from polynomial series, gives [29, 30]:
Tz=Ti+(ToTi)η(z) 

where:
ηz=1C2z+h2hkoiN+1ki2z+h2hN+1+koi22N+1ki22z+h2h2N+1koi33N+1ki32z+h2h3N+1+koi44N+1ki42z+h2h4N+1koi55N+1ki52z+h2h5N+1 

C=1koiN+1ki+koi22N+1ki2koi33N+1ki3+koi44N+1ki4koi55N+1ki5 

koi=koki 

In this study, the analytical solution of the heat conduction equation is also considered and the effect of this approach on the results is investigated. Temperature distribution across the shell thickness can be calculated analytically by considering boundary conditions and integrating the heat conduction equation as:
Tz=Ti+(ToTi)∫h/2h/2dzk(z)∫h/2zdzk(z) 

By definition:
NT=Nxx Nθθ Nxθ Mxx Mθθ Mxθ Qx Qθ
eT=εx,0 εθ,0 γxθ,0 kx kθ kxθ γxz,0 γθz,0 

The total strain energy of a cylindrical shell embedded in an elastic medium can be written as:
U=12∫0L∫02π NTeRdθdx+12∫0L∫02πk1w2+ks∂w∂x2+ks∂wR∂θ2Rdθdx 

where the second part of the above equation is related to the elastic foundation energy which is added to the strain energy of the shell.
k1, in force per unit volume, is the Winklerfoundation parameter, and ks, in moment per unit area, is the shear parameter of a Pasternak type of foundation.
Considering all inertia terms including the rotary inertia, the kinetic energy of a cylindrical shell is defined as:
T=12∫0L∫02πI1∂u∂t2+∂v∂t2+∂w∂t2+2I2∂u∂t∂ψx∂t+∂v∂t∂ψθ∂t+I3∂ψx∂t2+∂ψθ∂t2Rdθdx 

where inertia terms
I1,
I2 and
I3 are defined as:
I1=∫h/2h/2ρzdz, I2=∫h/2h/2ρzzdz,
I3=∫h/2h/2ρzz2dz 

The work done by compressive force Na and thermal force Nxxth can be calculated by [17, 31]:
W=12∫0L∫02π(NaNxxth)∂v∂x2+∂w∂x2Rdθdx 

Using Eqs. (15), (16) and (18) into Hamilton’s principle and performing lengthy mathematical manipulating, the governing equations of the cylindrical shell embedded in an elastic medium under thermomechanical loads can be expressed as:
∂Nxx∂x+1R∂Nxθ∂θ12R2∂Mxθ∂θI1∂2u∂t2I2∂2ψx∂t2=0 

∂Nxθ∂x+1R∂Nθθ∂θ+12R∂Mxθ∂x+1RQθ+NaNxxth∂2v∂x2I1∂2v∂t2I2∂2ψθ∂t2=0 

1RNθθ+∂Qx∂x+1R∂Qθ∂θ+NaNxxth∂2w∂x2k1w+ks∂2w∂x2+1R2∂2w∂θ2I1∂2w∂t2=0 

∂Mxx∂x+1R∂Mxθ∂θQxI2∂2u∂t2I3∂2ψx∂t2=0 

∂Mxθ∂x+1R∂Mθθ∂θQθI2∂2v∂t2I3∂2ψθ∂t2=0 

After substituting Eqs. (5) and (4) into Eqs. (1923), the shell equations of motion can be expressed in terms of the middle surface displacement components u, v,w, ψx, ψθ.
3. Method of solution
For the present study, only simply supported boundary condition at x=0 and x=L would be considered. A solution for the motion equations, satisfying boundary condition, can be described by:
u=Acosλxcosnθcosωt
v=Bsinλxsinnθcosωt w=Csinλxcosnθcos(ωt) ψx=Dcosλxcosnθcosωt ψθ=Esinλxsinnθcos(ωt) 

where λ=mπ/L;
A, B, C, D and E are the constants denoting the amplitudes of vibration; m and n are the axial and circumferential wave numbers, and ω(rad/s) is the natural angular frequency of the vibration.
Substituting the displacements model into Eqs. (1923) and application of Galerkin’s method, a set of equations is revealed as follows:
T11T12T13T14T15T21T22T23T24T25T31T32T33T34T35T41T42T43T44T45T51T52T53T54T55ABCDE=0 

where T_{ij }are some coefficients in which Na, Nxxth and ω have appeared (see Appendix A).
Eq. (25) is solved for natural frequencies and buckling loads (mechanical or thermal) of the shell by imposing the condition of nontrivial solutions and equating the characteristic determinant [Tij] to zero.
4. Numerical results and discussion
Some examples are provided to show the validity of the present study. The first verification is performed for a simply supported cylindrical shell surrounded by an elastic medium. The comparison is shown Fig. 2. It should be noted that Shah et al. [20] results are based on Love’s thin shell theories. It is observed that the present results are in excellent agreement with those in the literature.
Fig. 2. Variation of natural frequencies of a simply supported FG cylindrical shell; Pasternak foundation (λ=mπ/L, n=1, k_{1}=1e+7 N/m^{3}, L/R=20, h/R=0.002, E_{o}=2.07788×10^{11} Pa,υ_{o}=0.317756,ρ_{o}=8166 kg/m^{3}, E_{i}=2.05098×10^{11} Pa,υ_{i}=0.31,ρ_{i}=8900 kg/m^{3}, N=5).
The second comparison is concerned with the study of mechanical buckling load of a simply supported cylindrical shell. Results for an isotropic cylindrical shell are compared with Batdorf [32] and Ovesy and Fazilati [33] in Table 1 for axial loading. The good agreement between these results shows the high accuracy of the present work. It is seen from Table 1, in case of the lowest radius to thickness ratio (R/h=30) there is a small difference between the present results and those reported by the others. This might have occurred due to the different theories which are used in different studies. Ovesy and Fazilati [33] have used thin shell theory whereas FSDT is used in the current study.
Table 1. Buckling stresses (GPa) for various radius to thickness ratio (m=3, n=0, R=0.3 m, L=0.25 m, E=260 GPa, υ=0.3)
Method  R/h=30  R/h=100  R/h=300 
Batdorf’s Theory [32]  5.42  2.34  2.07 
Ovesy and Fazilati [33]  5.41  2.34  2.07 
Present  5.28  2.34  2.07 
Having validated the developed formulation in cases of free vibration (elastically supported or not), mechanical buckling load and thermal buckling temperature (uniform temperature rise), it is now time to focus on the case of nonuniform temperature distribution and investigating the effects of different methods for solving the heat conduction equation. As mentioned earlier in this paper, two different methods are applied to calculate temperature distribution through the shell thickness (series and analytical solutions). For this reason different FG plates are considered. The FG plates have metal on their inner surface and ceramic on their outer surface. The effective thermal conductivities for selected FGMs, calculated at 300 K, are listed in Table 2. It is considered that metal and ceramic surface temperatures are held in 300 K and 800 K, respectively.
Table 2. Thermal conductivities for selected FGMs
Material  Thermal conductivity (W/mK) 
Al//Zro2  204/2.09 
Al/Al2O3  204/10.4 
Ti6Al4V/Zro2  6.1/2.09 
Si3N4/SUS304  10.12/12.143 
Fig. 3 shows temperature distribution through the thickness of the considered FG plates based on the two above mentioned approaches, for different values of volume fraction exponents. It could be concluded from the graphs that the results of two approaches are different based on the FG configuration. In case of FG plates with materials in which thermal conductivities are close to each other (for example Si3N4/SUS304) there is a little difference between two methods, as expected for isotropic plate. Difference between two methods is decreased as difference between thermal conductivities of two constituent materials is decreased. It should be noted that, in the series approach, even by taking the first fourteen terms of series, the results are still surprisingly different from those obtained by the exact analytical solution. Ovesy et al. [25] have also reported that the results of polynomial series were different from those obtained from the analytical exact solution. Based on the obtained results it could be concluded that the series method may be applicable with sufficient accuracy for composition in which thermal conductivities of materials be close to each other.
Fig. 3. Temperature distribution through the thickness for a) Al/Zro2, b) Al/Al2O3, c) Ti6Al4V/Zro2 and d) Si3N4/SUS304.
Based on the two temperature distributions, vibration and stability behavior of FG simplysupported cylindrical shells will be studied and effects of the two different approaches on the results will be investigated. Consider a FG cylindrical shell with the following parameters (Aluminum and Zirconia are used in the inner and outer surfaces of the shell, respectively); Aluminum: E_{i}=70 GPa,υ_{i}=0.3,ρ_{i}=2707 kg/m^{3}, k_{i}=204 W/mK, α_{i}=23×10^{6} 1/^{◦}C and Zirconia: E_{o}=151 GPa,υ_{o}=0.3,ρ_{o}=3000 kg/m^{3}, k_{o}=2.09 W/mK, α_{o}=10×10^{6 }1/^{◦}C.
The following buckling load of the shell as suggested by Timoshenko and Gere [34] and nondimensional elastic foundation parameters are used in numerical results:
Ncr=Emh2R31υm2 , Kn1=k1R21υm2Emh ,
Kns=ks1υm2Emh 

where Em and υm are elastic modulus and Poisson’s ratio of the metal material respectively.
Fig. 4 shows the effects of thermal load on nondimensional fundamental frequency
Ω (Ω2=ω2R21υm2ρm/Em; ω denotes the fundamental frequency) for different nondimensional medium modulus parameters Kn1 and Kns. It is noted that the cylinder is subjected to an axial load of Na=0.5 Ncr. It is concluded from Fig. 4 that the nondimensional fundamental frequency decreases as the temperature difference between the inner and outer surfaces increases. The effects of elastic medium parameters and different approaches for temperature distribution on the nondimensional fundamental frequency are clearly demonstrated in the figures. Considering series solution instead of the analytical solution for temperature distribution leads to a smaller drop in frequency when temperature difference between the inner and outer surfaces increases.
Fig. 5 shows the effects of thermal load on critical axial load (Nacr/Ncr) of a simply supported FG cylindrical shell for different nondimensional elastic foundation modulus parameters Kn1 and Kns. As seen in Fig. 6, the critical axial load of the FG cylindrical shell decreases linearly as the temperature difference between the inner and outer surfaces increases, and the critical axial load increases as the medium modulus parameters increases. It is also observed that different approaches for temperature distribution have a significant effect on critical axial load.
a)
b)
Fig. 4. Nondimensional fundamental frequency (Ω) variation with temperature difference between the inner and outer surfaces (T_{oi}) and elastic foundation, m=n=1, N_{a}=0.5N_{cr}, L/R=1, h/R=0.01, N=2; a) Winkler parameter and b) shear parameter.
a)
b)
Fig. 5. Nondimensional buckling load (N_{acr}/N_{cr}) variation with temperature difference between the inner and outer surfaces (T_{oi}) and elastic foundation, m=n=1, N_{a}=0.5N_{cr}, L/R=1, h/R=0.01, N=2; a) Winkler parameter and b) shear parameter.
From Figs. 4 and 5 it can be stated that the effect of different approaches for calculation of temperature distribution is more significant for critical axial load than for fundamental frequency. Moreover, the more the effects of shear parameter with respect to Winkler parameter on nondimensional fundamental frequency and critical axial load are concluded from the graphs.
5. Conclusions
This paper reports the effects of mechanical and thermal loads on the vibration and stability of FG cylindrical shells embedded in an elastic medium, using two methods for throughthethickness temperature distribution. Based on the firstorder shear deformation theory of SandersKoiter and application of Hamilton’s principle, a system of equations is derived. Solution of these equations for a simply supported FG cylindrical shell which uses a power law distribution across the thickness coordinate is attempted by using Galerkin’s method. Extensive validation studies are performed for different cases of the problem. Having validated the developed methodology, the effects of two different solution approaches for heat conduction equation through the shell thickness on vibration and stability characteristics of FG cylindrical shells surrounded by an elastic medium under mechanical and thermal loads are then investigated: (i) polynomial series; (ii) analytical solution. The main conclusions are outlined below:
 Based on the FG configuration and composition, significant differences between temperature distributions through the thickness of the FG plates/shells calculated by polynomials series and exact analytical approaches may be exist, especially for higher values of volume fraction exponents (N).
 Based on the obtained results and also the popularity of polynomials series approach usage by many researchers, it can be noted that the series method may be applicable with sufficient accuracy in case of FG composition in which thermal conductivities of the materials be close to each other.
 The natural frequency of the considered FG cylindrical shell embedded in an elastic medium decreases as the temperature difference between the inner and outer surfaces increases, especially in the case of temperature distribution calculated by polynomials series.
 The natural frequency increases as the Winkler/shear modulus parameters of surrounding medium increases.
 The critical axial load of the considered FG cylindrical shell decreases linearly as the temperature difference between the inner and outer surfaces increases, especially with a dramatic drop for the case of temperature distribution calculated by polynomials series method.
 The critical axial load increases as the Winkler/shear modulus parameters of the surrounding medium increases.
 Shear parameter of elastic foundation has more effects on the nondimensional fundamental frequency and the critical axial load than Winkler parameter.
Appendix A
T11=A11m2π2L2+A66B66R+D664R2n2R2I1ω2 , T12=T21=A12+A66D664R2mnπLR
T13=T31=A12mπLR , T14=T41=B11m2π2L2+B66D662Rn2R2I2ω2
T15=T51=B12+B66D662RmnπLR , T22=A22n2+C551R2+A66+B66R+D664R2m2π2L2I1ω2
T23=T32=A22+C55nR2 , T24=T42=B12+B66+D662RmnπLR
T25=T52=B22n2R2+B66+D662Rm2π2L2C55RI2ω2
T33=A22+C55n2+ksn21R2+C44+NaNxxth+ksm2π2L2+k1I1ω2
T34=T43=B12R+C44mπL , T35=T53=B22RC55nR
T44=D11m2π2L2+D66n2R2+C44I3ω2 , T45=T54=D12+D66mnπLR
T55=D22n2R2+D66m2π2L2+C55I3ω2
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