In this study, the surface of a Piston Ring in the engine is coated with multilayered coating powder using plasma-spray technique, and its surface behavior is subsequently analyzed. The purpose of this study is to analyze the mechanical and thermal effects of surface coating for a Piston Ring during friction. Here specimens with and without coatings were prepared and then microstructure, hardness and corrosion tests were carried out. From the experimental results and Ansys results, it has been found that the coated specimen has improved the properties in improving the diesel engine performance. The results show less deformation and fewer scratches due to wear on the multilayer coated Piston Ring as compared to the uncoated one. The surfaces topography and the structure of the plasma spray coatings is observed on the scanning Electron microscope. The evaluation of the adhesion of coatings is made using the hardness test and also compared using the thermal barrier properties. Taking into account the results of measurements, one can state that the lowest wear and thermal resistance on piston rings by plasma spray coating.
In this research article, semiloof shell element was used to study the behaviour of plate and shells under mechanical and thermal load for stress, free vibration, initially stressed vibration, mechanical buckling, and non-linear vibration. In the above cases, the material properties: Isotropic, Composite and Functionally Graded Material (FGM) were considered. Wherein, the material property for the FGM shells was assumed to vary through the thickness of the shell by varying the volume fraction of the constituent, whereas, for composites, classical laminated theory was used. Utilizing the semiloof shell element, and the above material properties, the package COMSAP was developed. From the obtained results, we have observed that with coarse meshes, semiloof shell elements present better results, and it is especially effective in the case of thin plates and shells.
This work deals with the replacement of conventional two-piece steel drive shaft with a single-piece high strength composite drive shaft for an automotive application. The structural design parameters were optimized with the help of modelling software with the objective of minimizing the weight of composite drive shaft. The design optimization also showed significant potential improvement in the performance of propeller shaft. The modelling and analysis of the drive shaft [1] assembly was done using CATIA[2]/ANSYS software. Glass fiber reinforced polymer with silicon carbide is used in fabricating the propeller shaft. Finally, the analysis results were compared with conventional steel drive shaft.
The development of the friction stir welding being a solid state welding has provided an improved way of manufacturing aluminum joints in a quicker and reliable manner. The heat treatable aluminum alloy AA7075 is used substantially in the aerospace industry because of its high strength to weight ratio and good ductility. The objective of our work is to research the parameters of welding on the mechanical properties of friction stir welded joints of AA7075-T651. The parameters namely rotational speeds (500 rpm, 700 rpm, 900 rpm, 1100 rpm, 1300 rpm and 1500 rpm) were thought-about and table transverse speed of 50 mm/min, axial force of 8 KN is constrained throughout the welding process. The result of these parameters on weld quality is analyzed by its mechanical properties namely micro hardness and tensile strength.
Thermo-structural analysis with advanced composite plates and shells has been performed using Finite element method in order to determine temperature response and associated thermal stress. On solving the Fourier’s heat conduction equation, temperature profile is arrived at, with the assumption of linear/uniform temperature distribution through the thickness. Finite element program is developed for steady-state heat transfer problems using Semiloof shell element. Validation for integrated thermo-structural analysis has been done and compared with the available results from literature. The new results thus obtained are presented in terms of temperature, thermal stress, and displacement. The results obtained will be useful particularly in nuclear reactor vessels and Thermal Protection System (TPS) in aeronautical engineering.
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