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Sai Manohar

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Sai Manohar last won the day on June 2 2018

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  1. Version 1.0.0

    414 downloads

    The engineering project report presentation on Drag reduction using Aerospike. For more projects visit www.mechieprojects.com
  2. Version 1.0.0

    196 downloads

    The Full Project Report on Concept, Design & Working of Thermal Power Plants. It includes the major power plants in India too. For more projects visit: Mechanical Engineering Projects
  3. FULL PROJECT REPORT & PRESENATATION Abstract: When objects move through air, forces are generated by the relative motion between the air and surfaces of the object. Aerodynamics is the study of these forces, generated by the motion of air, usually aerodynamics are categorized according to the type of flow as subsonic, hypersonic, supersonic etc.Aerodynamic analysis of passenger vehicle exterior body has been an important area of interest since the time of the invention of automobiles. Initially, the analysis was done by making a complete car and running it on track. But measuring the experimental parameters was very difficult in external uncontrolled environment and also during the development stage there is no actual car to test so testing had to be done after an anticipated model of the car had been developed. The designers had to retrace the entire design process if they encountered any flaws in road test.It is essential that aerodynamics be taken in to account during the design of cars as an improved aerodynamics in car would attain higher speeds and higher fuel efficiency. For attaining this aerodynamic design the cars are designed lower to the ground and are usually sleek in design and almost all corners are rounded off, to ensure smooth passage of air through the body , in addition to it a number of enhancements like spoilers, wings are also attached to the cars for improving aerodynamics. Wind tunnels are used for analyzing the aerodynamics of cars , besides this a number of software‟s are also available now days to ensure the optimal aerodynamic design.
  4. Abstract: The term “Forging” is applied to processes in which a piece of metal is worked in a machine to the desired shape by plastic deformation of the starting stock. The energy that promotes deformation is applied by a hammer, press, up-setter or ring roller, either alone or in combination. The shape is imparted by the tools that contact the work piece and by careful control of the deformation process. A forging is produced in three distinct phases: stock preparation in the form of blooms, billets, bar or ingots; plastic deformation of the metal component to rough, close tolerance or net shape in one of the forging processes; and appropriate secondary operations Forged metal components are used in wide range of environment where high strength and reliability are important considerations. The use of forging is to reduce material wastage and machining time, avoids complex machining operations and for mass production. Forged components find application in the automobile/automotive industry and in aerospace, aircraft, railroad, and mining equipment. Metal forging process is governed by many factors such as friction, complexity of parts, die shape and temperature of die and billet. In this study we are going to learn about the principles of material selection, heat treatment, and the design calculations, which is involved in forging of metal This project is a study of the forging process, forgings defects, the forging machines and their applications. In this project we also consider the manufacturing of crane wheels through the closed die forging process in which metal is plastically reshaped using dies. This involves the steps like design and material selection based on its properties. Machinery equipment’s used in forging are pneumatic hammer forging machines, furnaces, dies, band saw machines etc. Closed die forging process is used to obtain the final product in close tolerance. The furnace is the main equipment in which the billet is preheated to a temperature of 1200 degrees centigrade and then forged into required shape. It offers a high strength-to- weight ratio, toughness, and resistance to impact and fatigue. Forgings_Report _ New.pdf
  5. ABSTRACT: The function of a rocket nozzle is to channelise and accelerate the combustion products produced by the burning propellant, inside a rocket motor, in such as way so as to maximize the velocity of the exhaust at the exit, to supersonic velocity. The nozzle converts the chemical energy of the propellant into kinetic energy with no moving parts. It is basically a tube with variable cross-sectional area. Nozzles are generally used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the exhaust stream that emerges from them. The nozzle is used to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature, thus producing the required thrust for the rocket to propel. The convergent and divergent type of nozzle is known as DE-LAVAL nozzle. Throat is the portion with minimum area in a convergent-divergent nozzle. The divergent part of the nozzle is known as nozzle exit. In the convergent section the pressure of the exhaust gases will increase and as the hot gases expand through the diverging section attaining high velocities from continuity equation. The analysis of a rocket nozzle involves the concept of "steady, one-dimensional compressible fluid flow of an ideal gas". The goal of rocket nozzle design is to accelerate the combustion products to as high an exit velocity as possible. This is achieved by designing the necessary nozzle geometric profile with the condition that isentropic flow is to be aimed for. Isentropic flow is considered to be flow that is dependant only upon cross-sectional area -- which necessitates frictionless and adiabatic (no heat loss) flow. Therefore, in the actual nozzle, it is necessary to minimize frictional effects, flow disturbances and conditions that can lead to shock losses. In addition, heat transfer losses are to be minimized. In this way, the properties of the flow are near isentropic, and are simply affected only by the changing cross-sectional area as the fluid moves through the nozzle. Space shuttle uses some of the largest De-Laval nozzles in the Solid Rocket Boosters(SRBs). They are designed so as to optimize the weight and the performance. In this project a study is conducted to study the various configurations and geometries of a De-laval nozzle w.r.t the available technologies been used in the world. Further an effort is made to analyse the flow of gases through a Space shuttle nozzle using commercially available software. www.mechieprojects.com DESIGN AND ANALYSIS OF SPACE SHUTTLE NOZZLE_New.pdf
  6. ABSTRACT: The function of a rocket nozzle is to channelise and accelerate the combustion products produced by the burning propellant, inside a rocket motor, in such as way so as to maximize the velocity of the exhaust at the exit, to supersonic velocity. The nozzle converts the chemical energy of the propellant into kinetic energy with no moving parts. It is basically a tube with variable cross-sectional area. Nozzles are generally used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the exhaust stream that emerges from them. The nozzle is used to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature, thus producing the required thrust for the rocket to propel. The convergent and divergent type of nozzle is known as DE-LAVAL nozzle. Throat is the portion with minimum area in a convergent-divergent nozzle. The divergent part of the nozzle is known as nozzle exit. In the convergent section the pressure of the exhaust gases will increase and as the hot gases expand through the diverging section attaining high velocities from continuity equation. The analysis of a rocket nozzle involves the concept of "steady, one-dimensional compressible fluid flow of an ideal gas". The goal of rocket nozzle design is to accelerate the combustion products to as high an exit velocity as possible. This is achieved by designing the necessary nozzle geometric profile with the condition that isentropic flow is to be aimed for. Isentropic flow is considered to be flow that is dependant only upon cross-sectional area -- which necessitates frictionless and adiabatic (no heat loss) flow. Therefore, in the actual nozzle, it is necessary to minimize frictional effects, flow disturbances and conditions that can lead to shock losses. In addition, heat transfer losses are to be minimized. In this way, the properties of the flow are near isentropic, and are simply affected only by the changing cross-sectional area as the fluid moves through the nozzle. Space shuttle uses some of the largest De-Laval nozzles in the Solid Rocket Boosters(SRBs). They are designed so as to optimize the weight and the performance. In this project a study is conducted to study the various configurations and geometries of a De-laval nozzle w.r.t the available technologies been used in the world. Further an effort is made to analyse the flow of gases through a Space shuttle nozzle using commercially available software. DESIGN AND ANALYSIS OF SPACE SHUTTLE NOZZLE_New.pdf
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