Design and construction of a simple turbojet engine

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Design and construction of a simple turbojet engine ( design-and-construction-simple-turbojet-engine )

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2.2.1 Reaction engines In order to provide thrust all aircraft engines work by imparting rearward momentum to one or more streams of gas, this gas is the reaction mass and such engines are known collectively as reaction engines. From Newtons laws of motion we know that force is equal to change in momentum, so net thrust, Fn for a jet engine can be written as follows, know as the general thrust equation [5]: Where m ̇ air m ̇ fuel Ve V0 Fn = (m ̇ a + m ̇ f )Ve − m ̇ aV0 (1) is the mass flow rate of the air passing through the engine is the mass flow rate of fuel entering the combustion chamber is the velocity of the exhaust stream (= V7) is the free stream velocity of the air coming in to the engine, same as the true airspeed of the aircraft Since m ̇ air >> m ̇ fuel we can make the simplification that the mass flow rate entering the engine is the same as the mass flow rate exiting the engine, and from there we get a simple expression for the propulsive efficiency, ηp, which is the ratio between the work done on the aircraft compared to the kinetic energy imparted to the air stream flowing through the engine: ηp= 2V0 = 2 (2) V0 + Ve 1 + Ve V0 From this the conclusion can be made that the highest efficiency is achieved when the velocity of the exhaust is nearly the same as that of the aircraft, shown in fig. 2. Using a larger mass flow rate instead of higher exhaust velocities is therefor preferable. De- pending on the range of speeds an aircraft is designed to operate in the preferred engine type varies, with slow aircraft the choice is propellers, followed by high-bypass turbofan and then progressively lower bypass ratios as the speed increases. [5] 6

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