1.1 Problem Summary and Introduction: In accordance with the invention, a turbocharger system comprises a turbocharger having a turbine wheel and a compressor wheel mounted on a common shaft and respectively received within turbine and compressor housings. The turbine and compressor housings are mounted on a center housing including bearings for rotatably supporting the shaft, and lubricant circulation passages for supplying a lubricant such as oil to the bearings. In operation, exhaust gases from a combustion engine rotatably drive the turbine wheel which correspondingly drives the compressor wheel to supply high density charge air to the engine. Conveniently, the engine includes a separate hydraulic system such as a lubrication system
Throttle valve A device that controls the flow of fuel and the power the engine makes. Sometimes a throttle valve is reffered to as a butterfly. As the gas pedal is depressed, the throttle opens allowing more air and fuel to enter the combustion chamber and resulting to more power. In a fuel injection system, this valve controls the flow of air only as the vehicle's on-board computer regulates the fuel
Lift and drag Lift is the component of the force that is perpendicular to the on coming flow direction. It contrasts with the drag force, which is the component of the surface force parallel to the flow direction . The lift and drag are the two primary factors to be considered for any aerodynamic analysis. In wind turbine blade analysis the lift force must be greater than drag force to improve the efficiency of the wind turbine. B.
Table 2 Advantages and disadvantages of different types of heat pumps Type of Heat Pump Advantages Disadvantages Vapor Recompression Proven technology with very good performance Simpler process (when compared to traditional compression) Recycle of produced vapour within the system (no need for external working fluid) Low operating cost Ease of design and operation Potential for high investment cost (although this is largely dependent on design) Potentially long payback times (unacceptable for industry deployment) Use of high grade energy (electricity / mechanical work) Possibility of leakage is a concern Vapour Compression Proven at industrial scale (mature technology) No major modifications to processes with implementation Useful with corrosive and fouling components Option to drive with mechanical energy or electrical energy Acceptable efficiencies (up to 60% of Carnot’s limit) Design dependent on the ability of the heat exchange fluid to meet stringent operational, environmental and safety
In this paper an attempt is made to study the Lift and Drag forces in a wind turbine blade for NACA4412 Airfoil profile is considered for analysis. In the present work, the numerical and experimentally analysis lift and drag performances of NACA 4412 airfoil at different attack angle for Reynolds numbers (Re) 3 ×105 by measuring
The sucked atmospheric air is compressed into the Compression Cylinder and then it is sent to the Power Cylinder. The system through which the compressed air is transferred to the Power Cylinder is known as Crossover Passage. The compressed air is then mixed with injected fuel and the combustion takes places in the Power
Engine inlet: Air enters the engines at supersonic speeds when a plane travels above Mach 1. A turbojet engine compressor—the rotating disks and blades at the face of the engine that compress the air before it is mixed with fuel—is unable to handle supersonic air flow. Thus, the purpose of an engine inlet is to slow incoming air to subsonic speeds before it flows through the engine. The spike, shaped like a cone, also gradually decreases the velocity of the incoming supersonic air without leading to a huge loss of pressure. As the air travels farther along the cone, the more speed it bleeds off.
INTRODUCTION The nozzle is a thrust producing component of a rocket or air-breathing engine. It helps in the conversion of the thermal energy into kinetic energy of the combustion engine and then direct it along the nozzle's axis. The fuel and the oxidiser are injected into the combustion chamber at a mass flow rate, m ̇ where they are mixed and burned. The exhaust is then pushed along the nozzle. They compress to a high pressure near the throat and gradually expand as the cross-sectional area increases.During this expansion process,they push against the wall contour,thereby producing thrust force.
#makh number:- the proportion of the rate of a body to the pace of sound in the encompassing medium. It is frequently utilized with a numeral (as Mach 1, Mach 2, and so on.) to demonstrate the rate of sound, double the rate of sound, and so forth. The significance of the speed of sound and makh number Mach number The Mach number is used to describe an airplane’s speed in terms of the speed of sound. A plane’s Mach number is determined by dividing the airplane’s speed by the speed of sound.