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Changes in temperature and pressure:
The changes in temperature and pressure of the gases through a gas turbine engine are illustrated in Figure 1.5 The efficiency with which these changes are made will determine to what extent the desired relations between pressure, temperature and velocity are obtained. The more efficient the compressor, the higher is the pressure generated for a given work input - i.e. for a given temperature rise of the gas. Conversely, the more efficiently the turbine uses the expanding gas, the greater is the output of work for a given temperature drop in gas.
VELOCITY AND PRESSURE
During the passage of the air (gas) through the engine, aerodynamic and energy requirements demand changes in its velocity and pressure. For example, during compression a rise in the pressure of the air is required with no increase in its velocity. After the air has been heated and its internal energy increased by combustion, an increase in the velocity of the gases is necessary to cause the turbine to rotate. Also at the propelling nozzle, a high velocity is required, for it is the change in momentum of the air that provides the thrust on the aircraft. Local decelerations of gas flow are also required - for example, in the combustion chambers to provide a low velocity zone for the flame.
Actuators The actuator consists of the control surfaces and associated servomechanisms, and is used to change the missile attitude and trajectory or flight path.
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Electro-mechanical fuel control: The start fuel valve and ignition are energised as soon as rotation (3%) is sensed by an Electronic Sequence Unit (ESU). At 14% and with risin
Principles of Jet Propulsion: Newton 's Laws of Motion. To understand the basic principles of jet propulsion it is necessary to understand the practical application of Sir I
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Parasitic resistances This is particularly noticeable if the transducer is a long way from where the power supply is located and if the transducer resistance is small.
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