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Experimental Investigation of Compound Pulse-Jet Engine

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Experimental Investigation of Compound Pulse-Jet Engine International Journal of Advanced Science and Engineering Research www.ijaser.in Volume: 3, Issue: 1, 2018 ISSN: 2455-9288 EXPERIMENTAL INVESTIGATION OF COMPOUND PULSE-JET ENGINE T.Mythili1, P.Sivakumar2,M.Saravana kumar3, M. Sabaree4 1.Asst Prof, Department of Aeronautical Engineering, Mahendra Engineering College,Namakkal India 2.Asst Prof, Department of Aeronautical Engineering, Mahendra Engineering College,Namakkal India 3.Student, Department of Aeronautical Engineering, Mahendra Engineering College,Namakkal India 4.Student, Department of Aeronautical Engineering, Mahendra Engineering College,Namakkal India Abstract The jet engines are either fuel consuming or have shortage of power. Thus we have created a new type of engine with a better design and less of drawbacks. The resultant jet engine is a hybrid of the pulsejet engine and turbojet engine. The combustion chamber of turbojet is replaced by pulsejet engine. The pulse jet used in a valveless pulsejet or thermojet. Since the combustion chamber and high pressure compressor blades are replaced with much simple pulsejet, thus the overall weight of the engine is reduced. The air entering the engine is divided into two parts, one passes along inner surface area of the turbojet casing and other part goes through the pulsejet for the combustion. The air passing though inner surface area acts as cooling medium for the pulsejet and will contribute for the thrust as it will increase the total mass flow rate at the downstream end of the engine. Mechanical efficiency of the engine will be increased as the moving mechanical parts will be decreased. Augmentor will be added later on for the pulse jet to increase the overall efficiency of the engine. If required a variant with afterburner can also be inducted. Keywords— pulsejet, thermojet, turbojet, turbojet, mass flow rate. 1. INTRODUCTION Among most of the jet engines many are fuel hungry engines and with soaring rise in fuel prices the operation of aerospace industry is getting costlier day by day. According to studies conducted by aerospace industries each and every ounce of weight reduction will result in increase in fuel economy. And some of the main drawbacks of a jet engine is that the maintenance is a very tedious job for commercial air liners as well as for the maintenance of military purpose aircraft jet engines The usual overhauling for the turbofan used in commercial airliners are in a range from 10000 – 30000 flying hours. Thus overhauling of a jet engine is very time consuming as well as resource consuming. Next with the increasing rate of accidents caused due to bird hits as well as foreign objects entering the jet engines usually in turbofan engines. These are the main drawbacks that we have kept in mind while developing this engine. 1.1.Basics Thus for the development of our hybrid engine these are the few basic but efficient type of engines of their kind, so for the knowledge of all we have provided aa overview of the basic engines that we have taken into consideration and conducted an extensive study about the given , different types of jet engines 1.1.1 Pulsejet Engine A pulse jet is defined as an engine in which pulse combustion happens. This engine is made of few or no moving parts. Its jet propulsion is in lightweight form having poor compression ratio & gives Copyright © 2018 by the Authors. This is an open access article distributed under the Creative Commons Attribution License, which permits 1040 unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. International Journal of Advanced Science and Engineering Research www.ijaser.in Volume: 3, Issue: 1, 2018 ISSN: 2455-9288 a low specific impulse. The notable research on this engine includes the impulse engine which has repeated denotations in it, which gives high compression and good efficiency. Fig-1 Working of valved pulse jet 1.1.2 Valveless Pulse Jet Valveless pulsejet engines consist of no moving parts. The exhaust flow comes out of the engine is controlled by using its geometry. These pulsejets release exhaust out of both the intakes and the exhaust, but it tries to expel the exhaust go out of the longer tail pipe for more efficient propulsion. The principle is as same as the valved pulsejets, but it is based on engine’s geometry. Fuel is given as a gas or as an atomized liquid spray. The fuel is passed by either mixing it with the air in the intake or directly injected into the combustion chamber.. The intake valve is used to intake the air & gets mixed it with the fuel to combust, which also controls the explosion of exhaust gas like a valve & limiting the flow but not stopping it altogether. The expanding gas while burning the air-fuel mixture is forced out of the exhaust pipe of the engine. During the exhaust cycle of the engine it also expels gas. The intakes are facing backwards in many valveless engines so that the thrust created add to the overall thrust, rather than reducing it. The combustion of valveless pulsejet creates two pressure wave fronts, one travelling down the longer exhaust tube & one down the short intake tube. A resonating combustion process can be achieved by properly tuning the system. Some valveless engines are extremely high in fuel consumption, while other designs use less fuel than a valved pulsejet, and a properly designed system with advanced components and techniques can rival or exceed the fuel efficiency of small turbojet engines. Copyright © 2018 by the Authors. This is an open access article distributed under the Creative Commons Attribution License, which permits 1041 unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. International Journal of Advanced Science and Engineering Research www.ijaser.in Volume: 3, Issue: 1, 2018 ISSN: 2455-9288 Fig-2 3D model of pulse jet Fig-3 working diagram of a valveless pulsejet 1.2 TURBOJET ENGINE Air intake A tube, or an air intake, is needed in front of the compressor to help it in directing the incoming air smoothly into the moving compressor blades. Stationary vanes are used in front of the moving blades in older engines that helped to direct the air onto the blades. The intake is also shaped to minimize any flow losses when the compressor is accelerating the air through the intake at zero and low aircraft speeds, and to slow the flow down for the compressor when the aircraft is operating above Mach 1. The air flowing into a turbojet engine must always be subsonic, regardless of the speed of the aircraft itself. Compressor Copyright © 2018 by the Authors. This is an open access article distributed under the Creative Commons Attribution License, which permits 1042 unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. International Journal of Advanced Science and Engineering Research www.ijaser.in Volume: 3, Issue: 1, 2018 ISSN: 2455-9288 The turbine drives the compressor which rotates at a high speed, adding energy to the airflow and it squeezes it into a smaller space. The pressure and temperature of the air is increased by compressing it. When the compressor is smaller, the turns are faster. Bleed air is extracted from the compressor section at various stages in most of the turbojet powered aircraft, to perform a variety of jobs including air conditioning pressurization, engine inlet anti- icing and turbine cooling. The efficiency of the engine is decreased by bleeding off the air, but the usefulness of the compressed air outweighs the loss in efficiency. There are two types of compressors are used in turbojets, axial & centrifugal. The overall pressure ratio is as low as 5:1 in early days. The splitting the compressor into two separately rotating parts by improvements made in aerodynamics, incorporating variable blade angles for entry guide vanes and stators, which has overall pressure ratios of 15:1 or more. The overall pressure ratios are 33:1 or more in modern civil turbofan engines. The air enters the combustion chamber after the compressor. Combustion chamber The process of burning in a combustor is different from that in a piston engine. The burning gasses are confined to a small volume in piston engine & as the fuel burns, the pressure increases. The air-fuel mixture in a turbojet is burnt in the combustor and passed through to the turbine bu a continuous flowing process without pressure buildup. Instead there is a small pressure loss in the combustor. The fuel-air mixture can only burn in slow moving air so an area of reverse flow is maintained by the fuel nozzles for the approximately stoichiometric burning in the primary zone. The combustion process is completed by introducing the compressor air & reduces thee temperature of the combustion products to a level which the turbine can accept. The combustion uses less than 25% of the air, & to keep the turbine limits, the overall lean mixture is used. Turbine Hot gases leaving the combustor expand through the turbine. Typical materials for turbines include inconel and Nimonic. The turbine vanes and blades have internal cooling passages. Air from the compressor is passed through these to keep the metal temperature within limits. The turbine is largely an impulse turbine in the first stage which rotates because of the impact of the hot gas stream. The gas is accelerated by convergent ducts in later stages. The energy transmission into the shaft is performed through momentum exchange in the opposite way that of the compressor. The compressor is driven by the power developed through turbines, as well as accessories like fuel, oil, and the accessory gearbox drives the hydraulic pumps.
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