In this research, a meshless numerical method has been developed to solve internal and axisymmetric flows. In this method, the least squares of the Taylor series are used for spatial discretization and explicit multi-step Runge-Kutta method is used for temporal discretization. Governing equations are based on two-dimensional and symmetric Euler equations. The second and forth order artificial dissipation are used to solve the flows. In order to model boundary condition, subsonic and supersonic inlet and outlet boundary conditions as well as the wall boundary have been used according to the problem. To validate the results of the code, the inviscid flow inside a two-dimensional nozzle and the supersonic flow inside the channel along with bump have been simulated and the results have been compared with valid data. The simulation of the steady flow inside a axi-symmetric convergent-divergent supersonic nozzle with Mach 5 in outlet has been done to measure the accuracy of solving the numerical code at the hypersonic speed. The results show that the developed code can simulate steady internal and axi-symmetric flows with very good accuracy. The process of code convergence is also presented, which shows the appropriate convergence of the developed code. The analysis time for shock capturing in the axi-symmetric nozzle is about 64% faster than the Fluent software.

The dynamic response of the leg (tether) of a Tension Leg Platform (TLP), subjected to AXIAL load at the top of the leg, is presented. The structural model is very simple, but several complicated factors, such as foundation effect, buoyancy and simulated ocean wave load, are considered. As an application, the effect of added mass fluctuation on the dynamic response of the leg subjected to such a load is presented. This effect is important in the fatigue life study of tethers. A first order perturbation method is used, in order to formulate and solve the problem. The differential equation is solved by means of non-harmonic Fourier expansion, in terms of eigenfunctions obtained from a non-regular Sturm-Liouville system.

The main purposes of the present work are devoted to the investigation of the free AXIAL vibration, as well as the time-dependent and forced AXIAL vibration of a SWCNT subjected to a moving load. The governing equation is derived through using Hamilton's principle. Eringen’ s nonlocal elasticity theory has been utilized to analyze the nonlocal behaviors of SWCNT. A Galerkin method based on a closed-form SOLUTION is applied to solve the governing equation. The boundary conditions are considered as clamped-clamped (C-C) and clamped-free (C-F). Firstly, the nondimensional natural frequencies are calculated, as well as the influence of the nonlocal parameter on them are explained. The results of both boundary conditions are compared together, and both of them are compared to the results of another study to verify the accuracy and efficiency of the present results. The novelty of this work is related to the study of the dynamic forced AXIAL vibration due to the AXIAL moving harmonic force in the time domain. The previously forced vibration studies were devoted to the transverse vibrations. The effect of the geometrical parameters, velocity of the moving load, excitation frequency, as well as the small-scale effect, are explained and discussed in this context. According to the lack of accomplished studies in this field, the present work has the potential to be used as a benchmark for future works.

This paper determines the buckling load of an axisymmetric cylindrical shell of homogeneous and isotropic materials analytically using the first-order shear deformation theory (FSDT). To describe the kinematics of the shell, the FSDT, and von Karman relations are used. The equilibrium equations, which are a system of nonlinear coupled differential equations, are determined from the principle of virtual work. The nonlinear equilibrium equations are solved analytically using the perturbation technique and then the stability equations are derived from them by employing the adjacent criterion method. The resulting equations are a system of coupled linear differential equations with variable coefficients that are solved analytically to find the buckling load of the structure. The effects of geometrical properties have been investigated by a parametric study on buckling load results. Also, the buckling load is determined using the finite element method (FEM) and classical theory (Lorenz) and compared with the analytical SOLUTION results.

This paper determines the buckling load of an axisymmetric cylindrical shell of homogeneous and isotropic materials analytically using the first-order shear deformation theory (FSDT). To describe the kinematics of the shell, the FSDT, and von Karman relations are used. The equilibrium equations, which are a system of nonlinear coupled differential equations, are determined from the principle of virtual work. The nonlinear equilibrium equations are solved analytically using the perturbation technique and then the stability equations are derived from them by employing the adjacent criterion method. The resulting equations are a system of coupled linear differential equations with variable coefficients that are solved analytically to find the buckling load of the structure. The effects of geometrical properties have been investigated by a parametric study on buckling load results. Also, the buckling load is determined using the finite element method (FEM) and classical theory (Lorenz) and compared with the analytical SOLUTION results.

The present study deals with the buckling analysis laminated composite truncated conical sandwich shells with flexible core subject to combined AXIAL compressive load and external pressure. The higher order governing equations of motion are presented for conical composite sandwich shells. They are derived from the Hamilton principle. Then, by use of Improved Higher-order Sandwich Shell Theory, the base SOLUTIONs of the governing equations are obtained in the form of power series via general recursive relations. The first order shear deformation theory is used for the face sheets and a 3D-elasticity SOLUTION of weak core is employed for the flexible core. By application of various boundary conditions such as clamped and simply-supported edges, the natural frequencies of the conical composite sandwich shell are obtained. The obtained results are compared with the numerical results from FEM analysis and good agreements are reached. An extensive parametric study is also conducted to investigate the effect of total thickness to radius ratio on the buckling load.

This paper deals with experimental results of an AXIAL compressor of a small power plant gas turbine engine. Tests were carried out during the engine operation (along operating line of the compressor). Time averaged AXIAL and radial pressure distributions in each individual stage were measured at different rotational speeds. Acceleration and deceleration phases of the engine were divided into reasonable time intervals of constant rotational speeds. Consequently, data logging was performed during steady operation of the engine. Measured parameters included pressure and temperature distributions and air mass flow rate. Test results were used to calculate AXIAL distribution of load factor along the compressor mean line. Experimental results showed that the span wise total pressure reduces from mean line region towards the hub and casing at each stage. No significant variations in load factor of each stage were observed during acceleration and deceleration phases of the engine. Meanline load factor distribution was increasing from compressor head towards its end within experimental rotational speed range.

In the present study, stress analysis and explicit SOLUTION of rectangular plate with arbitrarily located circular hole, subjected to linear normal stresses on two opposite edges, has been investigated. Airy function and hoop stresses occurring at the edge of the circular have been computed. In this method 2D dimension elasticity and Airy stress function was used. The present method for explicit SOLUTION and finding airy stress function are stronger and simpler than prior methods. By using Stress function, the stress distribution around circular hole were calculated. By using obtained airy stress relation the stress distribution around the circle was obtained, plotted and compared with distribution of stress (computed by finite element method in Abaqus). This comparison shows the accuracy of this SOLUTION method. It has been observed that stress distribution of stress function is independent from hole location and only depends on the hole's size.