logging in or signing up JET ENGINE mayankbhardwaj25 Download Post to : URL : Related Presentations : Let's Connect Share Add to Flag Embed Email Send to Blogs and Networks Add to Channel Copy embed code: Embed: Flash iPad Dynamic Copy Does not support media & animations Automatically changes to Flash or non-Flash embed WordPress Embed Customize Embed URL: Copy Thumbnail: Copy The presentation is successfully added In Your Favorites. Views: 1939 Category: Science & Tech.. License: All Rights Reserved Like it (1) Dislike it (0) Added: February 22, 2013 This Presentation is Public Favorites: 1 Presentation Description No description available. Comments Posting comment... Premium member Presentation Transcript Jet Engine Propulsion in Aircraft: Jet Engine Propulsion in Aircraft MAYANK BHARDWAJ 8MA1History Of Jet Engines: History Of Jet Engines The first jet engine was built by Egyptian scientists during 100 B.C. The device was known as Aeolipile and used steam power directed through two nozzles to cause a sphere to spin rapidly on its axis It was not used for supplying mechanical power and was simply considered a curiosity Dr. Hans von Ohain and Sir Frank Whittle were the pioneers behind today’s jet engines.Introduction: Introduction Jet engine is also called Gas Turbine Engine . It works under the principle of Newton’s third law which states that “ For every acting force there is an equal and opposite force. ’’PowerPoint Presentation: FAN COMPRESSOR COMBUSTOR TURBINE MIXER NOZZLE Main Components of Jet EngineWhat is a Jet Engine ?: What is a Jet Engine ? A jet engine is a machine designed for the purpose of creating large volumes of high velocity exhaust gases. This is done in order to overcome the aerodynamic drag of an airplane . In the process of producing high velocity exhaust, the engine also produces: Electrical Power Hydraulic Power Pneumatic power for air-conditioning & pressurization Hot Air for anti-icing protectionBasic Operation of a Jet Engine : Basic Operation of a Jet Engine The basic operations of Jet Engine are as follows : Air enters the compressor where it is compressed. Fuel is then added and ignited. The resulting gas spins the gas turbine. The turbine powers the compressor. The gas then exists the engine at tailpipe. The way a jet engine operates is similar To the way an automobile engine operates i.e. Intake Compression Ignition exhaustStructure of Jet Engine : Structure of Jet EngineStructure of Jet Engine : Structure of Jet Engine The engine shown below is known as Whittle Type Engine, since it follows the original design features developed by Sir Frank Whittle in the 1930’s. The first flight of a jet engine of his design was in 1941. All engines in use on today's commercial jet aeroplanes have been developed based on this original design.Types Of Jet Engines: Types Of Jet Engines Turbojet Turbofan Turboprop Turbo shaftPowerPoint Presentation: Pratt-Whitney Turbofan Engine Pratt Whitn ey Turbojet EngineTurbojet ENGINE: Turbojet ENGINE The turbojet engine is a reaction engine . A turbojet engine works by compressing air in compressor, mixing fuel with the compressed air, burning the mixture in the combustor, and then passing the hot, high pressure air through a turbine and a nozzle. Substantial increases in thrust can be further obtained by employing an afterburner Used in fighter planes, and were used in the Concorde. Turboprop ENGINE: A turboprop engine is a jet engine with a propeller attached in front. Majority of their thrust as in turbofan is obtained from propeller. However, it is efficient only up to certain height and speed. Turboprop ENGINE Turbofan ENGINE: Turbofan ENGINE A turbofan engine is a gas turbine engine which is similar to a turbojet. Turbofans differ from turbojets as they have an additional component, a fan. Fan in the engine produces as high as it 70-80 % of the total engine thrust without increasing fuel consumption because the fan air can exit separately from the core engine in other words 70-80% of the air is bypassed from core engine. It achieves this by increasing the total air-mass flow and reducing the velocity within the same total energy supply. Turbo SHAFT ENGINE: Turboshaft engines are very similar to turboprops, with a difference that nearly all energy in the exhaust is extracted to spin the shaft. They therefore generate little to NO jet thrust. This engine is used to drive shaft which in turn provides power to rotate helicopter rotor. The engine also has provision through Gear Box mechanism to maintain rotor speed constant even when the speed of the generator is varied . Turbo SHAFT ENGINEPowerPoint Presentation: The earliest commercial jet engine airplanes used a Single Spool turbojet engine like shown below. Structure of Jet Engine – Single SpoolPowerPoint Presentation: The term Single Spool refers to the fact that there is only one Shaft . This shaft connects the Turbine section to one compressor section . All Jet engines in current use are Axial Flow Engines meaning that the compression phases is done axially (parallel to the axis of the engine) as the airflows through the compressor. Structure of Jet Engine – Single SpoolPowerPoint Presentation: Thermodynamic Cycles Through a Jet Engine (Similar to a 4 Stroke Engine) ( suck) ( squeeze) (bang ) ( whoosh!)PowerPoint Presentation: The first significant development after the introduction of the early axial-flow, single-spool turbojets was the introduction of a second shaft . This second shaft allowed the engine to have two independent stages of compression powered by two independent turbines. Structure of Jet Engine – TWIN SpoolPowerPoint Presentation: P1, Page 11 The first stage of compression is the low-speed rotor and the second stage is the high-speed rotor. These terms refer to the fact that the first stage of the turbine, which rotates the second stage compressor, turns at a faster rate than the second stage turbine/ first stage compressor. These are often referred to as the N1 rotor (low-speed) and the N2 rotor (high-speed). Structure of Jet Engine – Twin SpoolPowerPoint Presentation: Turbofan Engine P1, Page 13 The bypass ratio is the ratio of the air which exits the engine without going through the rest of the engine core compared to the amount of air which goes through the engine core (the primary flow). Each of these produces thrust. Turbofan engines produce lower noise levels than earlier engines, and have considerably improved fuel economy .PowerPoint Presentation: High Bypass Ratio Turbofan Engine Early turbofan engines were “Low-Bypass ratio” engines. Approximately ½ of the thrust was produced by the fan stage, and the other half by the primary flow. Engines currently in production for most commercial airplanes are all high-bypass ratio turbofans. The difference is that these engines have a much higher ratio of bypass air compared to the primary air. In a typical turbofan engine with bypass ratios around 5:1 and higher, the fan stage provides about 75 to 80 percent of the total thrust produced by the engine . All bigger aero planes operating in India with M/s Air India. Jet Airways, Indigo, Spice jet are powered by Turbofan Engines.PowerPoint Presentation: High Bypass Ratio Turbofan Engine High bypass ratio engines take in a large amount of air and accelerate it only a small amount (relative to low bypass ratio engines). High Bypass Ratio Turbo Fan EnginePowerPoint Presentation: P1, Page 16 Rolls Royce Trent 800 engine bypass ratio - 6.5 :1 P & W PW 4084 e ngine: Bypass ratio - 6.8:1 High Bypass Ratio Turbo Fan Engines - few examplesPowerPoint Presentation: P1, Page 17 GE-90B engine B y pass ratio: 9:1 High Bypass Ratio Turbo Fan Engines – Another examplePowerPoint Presentation: P1, Page 18 High Bypass Ratio Turbo Fan EnginesPowerPoint Presentation: P1, Page 20 RR engines now in production use a triple-spool design incorporating three independent rotors. Triple Spool Turbofan Engines Designed to achieve better fuel economy due to the ability of the triple- spool design to better match the design of the compressors and turbines to the airflow .PowerPoint Presentation: Propulsive Efficiency The propulsive efficiency of an engine can be expressed in terms of the inlet velocity of the air and the exhaust velocity. V inlet V exit Jet Engine 2 X V inlet (V inlet + V exit ) ῃ p =PowerPoint Presentation: • An efficiency of 100% would be attained if the exhaust velocity was equal to the inlet velocity. However, for this to occur, the mass flow through the engine would need to be infinite. • Infinite mass flow is obviously not achievable in the real world, but this does indicate that greater efficiency is obtained when a large mass of air is accelerated by a small amount rather than a small mass of air being accelerated by a large amount. Propulsive EfficiencyPowerPoint Presentation: Propulsive EfficiencyPowerPoint Presentation: • From Newton's third law: – For every action there is an equal and opposite reaction • The jet engine's action is accelerating a mass of gas and sending it out tailpipe. • The equal and opposite reaction is thrust. The Thrust EquationPowerPoint Presentation: P1, Page 24 • Where: F w g V 1 V 2 is force in pounds is the gas flow in pounds per second is the gravitational constant is the initial velocity of the gas, in ft /sec is the final velocity of the gas, in ft /sec F = w g * (V 2 – V 1 ) From Newton’s second law: F = d(mv)/dt (= ma for a constant mass) • In jet engine terms, we can re-write this as: The Thrust EquationPowerPoint Presentation: We can re-write the thrust equation to make it more meaningful in the context of a jet engine: F net = w air + w fuel g X V jetexhaust V inlet X w air g - thrust of engine incoming velocity mass flow of incoming of air mass flow exhaust velocity total mass flow out tailpipe The Thrust EquationPowerPoint Presentation: • This is called the “Net” Thrust, because it accounts for the momentum of the incoming air; “Gross” Thrust is given by the first term in the equation – which is the force created at the exhaust of the engine. • To compute usable thrust, the gross thrust has to be reduced by the amount of the second term, which is the momentum already existing because of the airplane’s speed. • From the equation, it can be seen that net thrust is a function of the mass flow rate of the air and fuel passing through the engine, and of the exhaust velocity minus the incoming velocity. The Thrust EquationPowerPoint Presentation: Additional Thrust Due to Internal Pressure • This component of thrust is small compared to the thrust due to exhaust velocity, but should not be ignored. F = A exhaust X p exhaust - p ambient • The thrust equation as written is somewhat simplified in that it ignores one more possible component of thrust i.e. Thrust due to internal pressure. • Most of the internal pressure within the engine is converted to velocity of the exhaust gasses, which in turn produces thrust. • At the exhaust, if the total pressure of the gasses is greater than the total pressure at the intake, this surplus of pressure will produce some additional thrust.PowerPoint Presentation: Factors Affecting Thrust tropopause Air Temperature Thrust Altitude Thrust Air density, a function of temperature and pressure altitude, is a very significant component affecting thrust .PowerPoint Presentation: Airspeed % Thrust with out ram • Velocity affects both the momentum and the pressure of the air entering the engine intake. • Increasing aircraft speed increases the momentum of the incoming air, lowering thrust, while at the same time compressing the air at the intake (ram effect) increasing thrust by increasing density. The combined effect is show below. 100 % with ram 0% Factors Affecting ThrustPowerPoint Presentation: Other Factors Affecting Thrust Bleed air extraction affect thrust Power extraction for hydraulic pumps, electric generators, fuel pumps, etc., affects thrust. Humidity has a negligible effect on thrust.PowerPoint Presentation: Commonly used Jet Engine Terms • EPR - Engine Pressure Ratio: – Ratio of total pressure at the exhaust to total pressure at the front of the fan/compressor . – This is commonly used as a measure of engine thrust, and is the primary thrust setting parameter. • N1 or %N1: – N1 is the rotation rate, in RPM, of the low-speed rotor of a two or three-spool engine. – N1 is usually expressed as %N1, a percentage of some nominal value. – General Electric and CFMI engines use %N1 as the primary thrust setting parameter.PowerPoint Presentation: P1, Page 39 • Engine Stall (compressor stall): – A condition characterized by stalled airflow over the compressor blades. Surge: – Refers to a condition of unsteady airflow through an engine as the result of abnormal flow conditions. – Surge can result from strong crosswinds at low airspeeds (e.g., during takeoff) or other conditions such as very rapid acceleration or deceleration of the engine. Flameout: – A condition in which the combustion chambers lose their ignition. This could be the result of unsteady airflow (e.g., strong turbulence) or other conditions. Commonly used Jet Engine TermsPowerPoint Presentation: Other Commonly Encountered Jet Engine Terms • Bleed: – Extraction of compressed air from the engine. – Bleed air is used for air conditioning and pressurization, as well as for providing icing protection. – Engine bleeds are also used in some cases to prevent surging. • EGT – Exhaust Gas Temperature: – This is the temperature at the engine exhaustADVANTAGES OF JET ENGINES: ADVANTAGES OF JET ENGINES Gas turbine engines have a great power-to-weight ratio compared to reciprocating engines. That is, the amount of power you get out of the engine compared to the weight of the engine itself is very good. Gas turbine engines are smaller than their reciprocating counterparts of the same power. Jet engine designs are frequently modified for non aircraft applications, as industrial gas turbines . These are used in electrical power generation, for powering water, natural gas, or oil pumps, and providing propulsion for ships and locomotives. Industrial gas turbines can create up to 50,000 shaft horsepowerDISADVANTAGES OF JET ENGINES: DISADVANTAGES OF JET ENGINES Compared to a reciprocating engine of the same size, they are expensive . Because of high speeds and high operating temperatures, designing and manufacturing gas turbines is a challenge from both the engineering and materials point of view. Gas turbines also tend to use more fuel when they are idling.Thank You…: Thank You… You do not have the permission to view this presentation. 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