Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space

75 Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space Abstract In this work we consider a problem in the contet of the generalized theory of thermoelasticity for a half space. The material of the half space is functionally graded in which Lamé s modulii are functions of the vertical distance from the surface of the medium. The surface is traction free and subjected to a time dependent thermal shock. The problem was solved by using the Laplace transform method together with the perturbation technique. The obtained results are discussed and compared with the solution when Lamé s modulii are constants. Numerical results are computed and represented graphically for the temperature, displacement and stress distributions. Keywords Half Space; Generalized Thermoelasticity; Perturbation method; FGM; Variable Lamé s modulii. Hany H. Sherief a A. M. Abd El-Latief b a Aleandria University, Egypt, HanySherief@gmail.com b Aleandria University, Egypt, m.abdellatief@yahoo.com http://d.doi.org/0.590/679-785086 Received 6.04.05 In revised form 0..05 Accepted 06.0.06 Available online 7.0.06 INTRODUCTION The theory of generalized thermoelasticity with one relaation time was introduced by Lord and Shulman (967). In this theory Cattaneo-Mawell law of heat conduction replaces the conventional Fourier s law. The heat equation associated with this theory is a hyperbolic one and hence automatically eliminates the parado of infinite speeds of propagation inherent in both the uncoupled and the coupled theories of thermoelasticity. For many problems involving steep heat gradients and when short time effects are sought this theory is indispensable. Sherief and El-Maghraby (003, 005) solved some crack problems for this theory. Sherief and Hamza has obtained the solution of aisymmetric problems in cylindrical regions in (994) and in spherical regions in (996). Sherief and Ezzat (994) have obtained the solution in the form of series. Sherief and Dhaliwal (98) used asymptotic epansions to obtain the solution of a D problem and to find the locations of the wave fronts and the speed of propagation of thermoelastic waves. This theory was etended to deal with thermoelastic diffusion in (004), micropolarity of the medium in (005), viscoelastic effects in

76 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space (0). Sherief et.al (00) etended this theory using fractional derivatives. Under this theory, Sherief and Abd-Ellatief (03, 04a, 04b) have solved some problems. Functionally graded materials (FGMs) are a new class of materials with the material properties varying continuously along specified directions. Due to their desirable properties, FGMs have been increasing used in modern engineering applications (Wang(03)). For eample, the functionally graded metal-ceramic composites have been used as thermal barriers or thermal shields in various applications(lee et.al(996), Tsukamoto(00)). Especially, Praveen et.al. (999) in severe temperature environments, such as etremely high temperature and thermal shock, widely potential applications are opening for FGMs. In recent years, Asgari and Akhlaghi (009) composition of several different materials is often used in structural components in order to optimize the thermal resistance and temperature distribution of structures subjected to thermal loading. Other works that consider FGM can be found in (Nahvi et.al. (008), Zafarmand et. al. (05), Dey et.al. (05)). FORMULATION OF THE PROBLEM In this work, we consider a homogeneous isotropic thermoelastic solid occupying the region 0 composed of a FGM material whose Lamé's parameters depend on the vertical distance '' '' from the surface. The surface of the half-space is taken to be traction free and is subjected to a thermal shock that is a function of time. We assume also that there are no body forces or heat sources inside the medium. The initial conditions are assumed to be homogenous. From the physics of the problem, it is clear that all the variables depend on and t only. The displacement vector will thus have the form. The equation of motion is given by u u(, t),0,0 () u t () where is the normal component of the stress tensor given by u ( ) (3 ) t (3) where, are Lamé's modulii. t is the coefficient of thermal epansion and T T0 where T is the absolute temperature, T0 is the temperature of the medium in its normal state such that. Substituting from Equation (3) into Equation (), we get Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 77 u ( ) (3 ) t u u t 3 t (4) where is the density. The equation of the heat conduction has the form u k 0 C E T0(3 ) t t t (5) where C E is the specific heat per unit mass in the absence of deformation, k is the thermal conductivity and 0 is the relaation time. From now on, we shall take, in the form a e, e (6) a 0 0 where 0, 0 and a are constants. Thus equations (3-5) take the form a u a ( 0 0) e (3 ) t e u a u a ( 0 0) e (30 0) t e t a u k 0 C E T0(30 0) t e t t (7) (8) (9) We shall use the following non-dimensional variables c, u' cu, t c t, τ c τ, a' a/ c ' ' ' 0 0 σ (3λ μ ) λ μ ρc,,, λ μ λ μ ρ k ' ' 0 0 t 0 0 σ θ c η 0 0 0 0 Using the above non-dimensional variables, equations (7)-(9) take the form E e a u (0) u t u a e () Latin American Journal of Solids and Structures 3 (06) 75-730

78 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space a u 0 e t t () The remaining components of the stress tensor are given by: a ( ) u yy zz e (3) y z yz 0 (4) ( 0 0) where T0 (30 0) t /( 0 0) k, 0 We assume that the boundary conditions have the form (0, t) f ( t), (, t) 0, t 0 (5) where f(t) is a known function of t (0, t) (, t) 0, t 0 (6) 3 SOLUTION IN THE LAPLACE TRANSFORM DOMAIN Applying the Laplace transform with parameter s defined by the relation st f (, s) e f (, t) d t to both sides of equations (0)-(3), we get the following equations 0 e a u (7) e a u s u (8) a s 0s e u (9) a ( ) u yy zz e In order to solve the above equations, we shall use the perturbation method. We epand the temperature, displacement and stress functions as follows: Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 79 where andu ( i ) ( i ) () () a a u u au a u () () () () a a are functions to be determined, i = 0,, Equations (8-9) gives, upon equating the coefficients of a in both sides up to order......... u s u () u u () () () s u s u () ( ) u s 0s (3) ( ) u u ( ) () () () s 0s s 0s (4) Using epansion of equation (7), we obtain u u () () () (5) (6) Eliminating between equations () and (3), we get 4 3 D D s ( ) s( τ 0s) s ( τ 0s) u 0 (7) where D The general solution of equation (7) which is bounded at infinity can be written as k k u k A e k A e (8) where A and A are parameters depending on s only and k and k are the roots with positive real parts of the characteristic equation Latin American Journal of Solids and Structures 3 (06) 75-730

70 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space 4 3 k k s ( )( τ0s) s s ( τ0s) 0 From equations () and (8), we get k k ( ) ( ) A k s e A k s e (9) The boundary conditions (5-6) give f ( s), at 0 (30a) () 0, at 0 (30b) u 0, at 0 (30c) () u () 0, at 0 (30d) In order to determine A, A we shall use the boundary conditions (30a), (30c) to obtain Equations (8), (9) become A A f ( s ) k k u k k k e k k [ ke ] f () s (3) Eliminating u () k k k k [( k s ) e ( k s ) e ] f(s) between Eq. () and Eq. (4), we get 4 D D s ( ) s( τ s) s ( τ s) 3 () 0 0 s 0s D ( s D ) D u (3) (33) Substituting from equations (3-3) into the right hand side of equation (33) and factorizing the left hand side as before, we obtain () ( ) k D k D k C E e ( C E) e k (34) Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 7 where,, C k s s s k A E k s s k s A 0 0 C k s s s k A E k s s k s A 0 0 The solution of the above non homogenous differential equation takes the form () k k k k B e B e ( F G) e ( F G) e (35) where B and B are unknown parameters depending on s while the remaining parameters, due to the particular solution, are given by C 5k k F, G E C 4kk k kk k kk k C 5k k F, G E C 4k k k k k k k k k By the same manner the displacement differential equation takes the form () ( ) k D k D k u H P e ( H P) e k (36) where, 3, 3 H s 0s s k s ka P k s s 0s A H s 0s s k s ka P k s s 0s A The solution of Eq. (36) is given by () k k k k ( ) ( ) u L e L e M N e M N e (37) where L and L are unknown parameters depending on s while the remaining parameters, due to the particular solution, are given by H 5k k M, N P H 4kk k kk k kk k H 5k k M, N P H 4k k k k k k k k k Substituting form Eqs. (8), (35) and (37) into Eq. (4), comparing the coefficient of the eponentials in the resulting equation, we get Latin American Journal of Solids and Structures 3 (06) 75-730

7 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space L s s N s s k B G 0 0 k s 0s L s s N s s k B G 0 0 k s 0s (38a) (38b) Substituting from Eqs. (35), (37) into the boundary conditions (30b), (30d), we obtain Solving the above system, we obtain B B (38c) kl k L N N (38d) B G G k k (39) The other constants can be easily obtained from equation (38a, b,c). Thus we have the solution in the Laplace transform domain for the temperature and displacement functions. The stress can be determined from Eqs. (5-6). The solution in the physical domain can be obtained by using numerical inversion method outlined in (Honig and Hirdes (984)). This method has been successfully used in solving many problems in the theory of thermoelasticity (see e.g. (Sherief and Megahed (999)), (Sherief and Anwar (988)) 4 NUMERICAL RESULTS AND DISCUSSION The copper material was chosen for purposes of numerical evaluations. The constants of the problem are shown in table k =386 W/(m K) t =.78 (0) -5 K - ce = 38 J/(kg K) = 8886.73 0 =3.86 (0) 0 kg/(m s ) 0 = 7.76 (0) 0 kg/(m s ) = 8954 kg/m 3 T0 = 93 K = 0.068 0 = 0.05 s a = 0.3 m - b = 0.04 s Table : The material constants. The computations were carried out for different functions f(t). We have chosen the following two cases: Case t bs sin 0 t b b( e ) f () t f () t b,givingf (s) bs 0 otherwise Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 73 Case f () t f () t H (), t which gives f (s) s The temperature, displacement and stress components were calculated by using the numerical method for the inversion of Laplace transform illustrated in Honig and Hirdes (984). The FORTRAN programming language was used on a personal computer. The accuracy maintained was 5 digits for the numerical program. 4. FIGURES and Discussion Figures () and () show the temperature distribution for t = 0. for cases and, respectively. In these figures and subsequent ones the dotted lines denote the case of constant Lamé s modulii (CL) while solid lines represent the case of variable Lamé s modulii (VL). We note that changing of Lamé s modulii has very small effect on the temperature profile. 0. 0.5 0. 0. 0. 0. 0. θ V CL 0. 0.4 0.6 0.8.0 Figure : Temperature Distribution (Case )..0 0.8 θ VL CL 0.6 0.4 0. 0.0 0. 0. 0. 0.. Figure : Temperature Distribution (Case ). Latin American Journal of Solids and Structures 3 (06) 75-730

74 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space Figures (3) and (4) show the displacement distribution for t = 0. for cases and, respectively. We note that an increase in the values of Lamé s modulii results in an increase in the value of the displacement. 0.0 0.0 0.00-0.0-0.0-0.03-0.04-0.05-0.06 u VL CL 0. 0.4 0.6 0.8.0 Figure 3: Displacement Distribution (Case ). 0.0 0.00-0.0-0.04-0.06-0.08-0.0 u VL CL 0. 0.4 0.6 0.8.0 Figure 4: Displacement Distribution (Case ). Figures (5) and (6) show the stress distribution for t = 0. for cases and, respectively. We note that an increase in the values of Lamé s modulii results in a decrease in the value of the stress component. Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 75 0.8 0.6 0.4 0. 0.0-0. -0.4-0.6-0.8 θ VL CL 0. 0.4 0.6 0.8.0 Figure 5: Stress Distribution (Case ). 0. 0.0-0. -0.4-0.6-0.8 - θ VL CL 0. 0.4 0.6 0.8.0 Figure 6: Stress Distribution (Case ). Figures (7-) show the distributions of θ, u and σ for different times. In these figures the solid lines and the dotted lines represent t = 0.08 and t = 0., respectively. We note that the increase of the time results in an increase in the thermal wave penetration into the medium. The same effect is noticed for the displacement and the stress distributions. 0.8 0.6 θ t = 0.08 t = 0. 0.4 0. 0.0 0. 0.4 0.6 0.8.0 Figure 7: Temperature Distribution (Case ). Latin American Journal of Solids and Structures 3 (06) 75-730

76 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space..0 0.8 0.6 0.4 0. 0.0 θ t = 0.08 t = 0. 0. 0.4 0.6 0.8.0 Figure 8: Temperature Distribution (Case ). 0.0 0.0 0.00-0.0-0.0-0.03-0.04-0.05-0.06 u t = 0.08 t = 0. 0. 0.4 0.6 0.8.0 Figure 9: Displacement Distribution (Case ). 0.04 0.0 0.00-0.0-0.04-0.06-0.08-0.0 u t = 0.08 t = 0. 0. 0.4 0.6 0.8.0 Figure 0: Displacement Distribution (Case ). Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 77 0.8 0.6 0.4 0. 0.0-0. -0.4-0.6-0.8 θ t = 0.08 t = 0. 0. 0.4 0.6 0.8.0 Figure : Stress Distribution (Case ). 0. 0.0-0. -0.4-0.6-0.8 - θ t = 0.08 t = 0. 0. 0.4 0.6 0.8.0 Figure : Stress Distribution (Case ). Comparison between the values of all the functions are shown in tables -4. Case Case with VL with CL with VL with CL 0.0 0.00096 0.00096.00000.00000 0. 0.45885 0.45885 0.83995 0.833987 0. 0.55754 0.55754 0.674497 0.674486 0.3 0.483596 0.483596 0.545 0.546 0.4 0.3600 0.3600 0.3874 0.38743 0.5 0.45895 0.45895 0.6636 0.6640 0.6 0.04537 0.04537 0.6433 0.64365.0 0.000000 0.000000 0.000000 0.000000 Table : Temperature Values for t = 0.. Latin American Journal of Solids and Structures 3 (06) 75-730

78 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space Case Case u with VL u with CL u with VL u with CL 0.0-0.05336-0.04940-0.080899-0.07783 0. 0.003 0.0565 0.0664 0.08645 0. 0.006049 0.00709 0.0097 0.00863 0.3 0.00754 0.00337 0.004668 0.005794 0.4 0.000968 0.0036 0.00083 0.00696 0.5 0.0000 0.00080 0.00078 0.000968 0.6 0.000008 0.0000 0.000099 0.00039.0 0.000000 0.000000 0.000000 0.000000 Table 3: Displacement Values for t = 0.. Case Case with VL with CL with VL with CL 0.0 0.0 0.0 0.0 0.0 0. -0.47895-0.48803-0.58075-0.95607 0. -0.56944-0.603679-0.68690-0.7374 0.3-0.4679-0.5436-0.507448-0.563973 0.4-0.880-0.330666-0.356693-0.40386 0.5-0.7300-0.574-0.33853-0.785 0.6-0.045-0.046068-0.37480-0.6943.0 0.0 0.0 0.0 0.0 Table 4: Stress Values for t = 0.. As usual in dealing with problems of the theory of generalized thermoelasticity, the finite speed of wave propagation is apparent. For t = 0. the solution is identically zero for > 0.634, approimately, for both cases. We note that for case, the temperature and stress distributions have two discontinuities. The first discontinuity is at = 0.973 approimately while the second discontinuity is at = 0.634 approimately. The first discontinuity in the temperature is very small in value and does not show in the figure. The displacement distribution is continuous but has discontinuous first derivatives at the above locations. These locations are the locations of the wave fronts. These discontinuities are due to the fact that the input thermal shock f (t) is a discontinuous function. For case, where the thermal shock is represented by a continuous function f (t), all the considered functions are continuous. The temperature and stress have discontinuous first derivatives at the wave fronts. Latin American Journal of Solids and Structures 3 (06) 75-730

H.H. Sherief and A.M.A. El-Latief / Modeling of Variable Lamé s Modulii for a FGM Generalized Thermoelastic Half Space 79 References Asgari, M., Akhlaghi, M., (009). Transient heat conduction in two-dimensional functionally graded hollow cylinder with finite length. Heat Mass Transfer 45: 383 39. Dey, S., Adhikari, S., Karmakar, A., (05). Impact response of functionally graded conical shells. Lat Am J Solids Stru. ():33-5. Honig, G., Hirdes, U., (984). A Method For The Numerical Inversion of the Laplace Transform. J Comp Appl Math 0:3-3. Lee, W., Stinton, D., Berndt, C., Erdogan, F., Lee, Y., Mutasim, Z., (996). Concept of functionally graded materials for advanced thermal barrier coating applications. J Am Ceram Soc. 79: 3003 30. Lord H., Shulman, Y., (967). A Generalized Dynamical Theory Of Thermo- elasticity. J Mech Phys Solid 5: 99-309. Nahvi, H., Salehipour, H., Shahidi, A., (008). Generalized coupled thermoelasticity of functionally graded annular disk considering the Lord Shulman theory. Composite Structures 83:68-79. Praveen, G., Chin, C., Reddy, J., (999). Thermoelastic analysis of functionally graded ceramic-metal cylinder. J Eng Mech. 5: 59 67. Sherief, H., Abd El-Latief, A., (03). Effect of variable thermal conductivity on a Half-Space under the Fractional order Theory of thermoelasticity. Int J Mech Sci 74: 85-89 Sherief, H., Abd El-Latief, A., (04a). Application of Fractional order Theory of thermoelasticity to a D Problem for a Half-Space. ZAMM 94: 509 55. Sherief, H., Abd El-Latief, A., (04b). Application of fractional order theory of thermoelasticity to a D problem for a half-space. Appl Math Computation 48: 584-59 Sherief, H., Allam, M., El-Hagary, M., (0). Generalized theory of thermoviscoelasticity and a half-space problem. Int J Thermophys 3:7 95 Sherief, H., Anwar, M., (988). A problem in generalized thermoelasticity for an infinitely long annular cylinder, Int. j. engng. sci 6: 30-306 Sherief, H., Dhaliwal, R., (98). A generalized one-dimensional thermal shock problem for small times. J Thermal Stresses 4: 407 40. Sherief, H., El-Maghraby, N., (003). An internal pennyshaped crack in an infinite thermoelastic solid. J Thermal Stresses 6: 333 35 Sherief, H., El-Maghraby, N., (005). A mode-i crack problem for an infinite space in generalized thermoelasticity. J Thermal Stresses 8: 465 484 Sherief, H., El-sayed, A., Abd El-Latief, A. (00) Fractional order theory of thermoelasticity. Int J Solids Structures 47: 69-75. Sherief, H., Ezzat, M., (994). Solution of the generalized problem of thermoelasticity in the form of series of functions. J Thermal Stresses 7: 75 95 Sherief, H., Hamza, F., (994). Generalized thermoelastic problem of a thick plate under aisymmetric temperature distribution. J Thermal Stresses 7: 435 45 Sherief, H., Hamza, F., (996). Generalized two-dimensional thermoelastic problems in spherical regions under aisymmetric distributions. J Thermal Stresses 9: 55 76 Sherief, H., Hamza, F., El-Sayed, A., (005). Theory of generalized micropolar thermoelasticity and an aisymmetric half-space problem. J. Thermal Stresses 8: 409-437. Sherief, H., Hamza, F., Saleh, H., (004). The theory of generalized thermoelastic diffusion. Int J Engng Sci. 4: 59-608. Latin American Journal of Solids and Structures 3 (06) 75-730

730 H.H. Sherief and A.M.A. El-Latief / Modeling of Variable lamé s Modulii for a FGM Generalized Thermoelastic Half Space Sherief, H., Megahed, F., (999). A two-dimensional thermoelasticity problem for a half space subjected to heat sources, Int. j. solids struct. 36: 369-38 Tsukamoto, H., (00). Design of functionally graded thermal barrier coatings based on a nonlinear micromechanical approach. Comput Mater Sci. 50: 49 436. Wang, H., (03). An effective approach for transient thermal analysis in a functionally graded hollow cylinder. Int J Heat Mass Transfer 67: 499 505. Zafarmand, H., Salehi, M., Asemi, K., (05). Theree dimensional free vibtation transient analysis of two directional functionally graded thick cylinderical panels under impact loading. Lat Am J Solids Stru. ():05-5 Latin American Journal of Solids and Structures 3 (06) 75-730