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Publication Title | Performance Analysis of Jet Engine of Aircraft

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Search Completed | Title | Performance Analysis of Jet Engine of Aircraft
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Where Vj is now the velocity of the gas stream at the propelling nozzle. This represents a simplified version of the full thrust equation as the majority of thrust produced is a result of the momentum change of the gas stream.
Figure 2 - Direction of Flight vs. Direction of Propeller
Figure 3 - Jet Thrust - Relative Velocities
C. Power unit and working cycle of jet engine
Power Unit
The aircraft is powered by an ORPHEUS-70105 engine. The engine is a straight flow turbo-jet type, fitted with a 7-stage axial flow compressor and develops 4200 ± 84 Ibs/ 1909 + 38 kg static thrust at 9500 rpm at sea level. This increases to a maximum at 10, 000 ft, due to the characteristics of the high pressure fuel pump in the engine fuel system. Above this height the thrust developed reduces as altitude increases. The engine change unit includes air driven starter, switches for low-pressure fuel and oil pressure warning indicators and all engine driven accessories except the main electrical generator and hydraulic pump[14],[16],[18].
Engine Working Cycle
Air at atmospheric pressure is compressed adiabatically, during its passage across the compressor and diffuser, to approximately four atmospheres. The pressure and temperature increases and volume decreases at this stage. In the combustion chamber, heat is supplied at constant pressure there by considerably increasing the volume of air. Then during the passage of the gas stream through the rear end of the combustion chambers, stationary vanes, turbine and exhaust cone, there is adiabatic expansion, which is completed in the propelling nozzle with increased volume and decreased pressure. At the end of propelling nozzle, there is rejection of heat at constant pressure.
Air flowing through the engine follows a straight path. Air entering in to the air intake duct is directed by entry guide blades at the rear of the air intake casing into the compressor,
Performance Analysis of Jet Engine of Aircraft
where in temperature and pressure increases progres¬sively with its passage through the seven stages to the delivery casing. Air discharged from the delivery casing enters the combustion chambers, where it is mixed with the atomized fuel sprayed from the burners. Initially, the mixture is ignited by the igniter plugs. The continuous combustion inside the combustion chamber raises the temperature and velocity (but not the pressure) of the gas. Immediately after the combustion zone, air is introduced to reduce the gas temperature to a value compatible with the limits of the turbine blade mate¬rial from the combustion chambers, the velocity of the gas increases due to the nozzle effect between adjacent stator blades. A further increase in velocity occurs as the pressure and temperature fall during the passage through the turbine wheel blades. The high velocity gases impinging on the combined impulse and reaction type blades turn the turbine wheel. The power generated by the turbine is absorbed primarily in driving the compressor to pressurize the incoming air, only a small portion being utilized to drive the auxiliary equipment and accessories. On leaving the turbine, the velocity continues to increase and pressure and temperature falls, the ultimate velocity being reached as the gases pass out of the exhaust cone into the jet pipe.
Working Cycle
A gas turbine is basically a warmth motor utilizing air as a liquid to create push. The working cycle of the gas turbine is like that of a cylinder motor and both motor cycles have enlistment, pressure, ignition and fumes stages. Anyway a gas turbine can manage a lot bigger measures of vitality for a given size and weight, and it has the additional preferred position that the mechanical movement is consistent and totally rotational, while the cylinder motor uses a discontinuous responding movement which is changed over to revolving movement by methods for wrenches. In result the gas turbine runs all the more easily.
The gas turbine cycle can be spoken to by a temperature/entropy (T/S) outline. (Entropy is a proportion of turmoil; the more noteworthy the entropy or level of confusion in the gas, the less work can be extricated from it.) Referring to, Point 1 speaks to the passage to the blower; the air experiences adiabatic pressure along the line 1-2. Warmth is added to the air through consuming fuel which causes consistent weight warming along the line 2-3. Adiabatic development through the turbines, line 3-4, extricates vitality from the gas stream to drive the blower and perhaps a propeller, fan or rotor framework.
Published By:
Blue Eyes Intelligence Engineering 607 & Sciences Publication
Retrieval Number: F11790886S219/2019©BEIESP DOI:10.35940/ijeat.F1179.0886S219

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