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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chamber, turbine and nozzle. There are also numbered station which are used for de- scribing the state of the flow at different points in the engine. A schematic view is shown in figure 3. The zeroth station is far enough up stream before the intake that ambient conditions apply. The region between stage one and two is the diffuser, where the stream is slowed down, and the pressure rises. The region between 2 and 3 is the compressor, where energy is added to the flow, idealized as an adiabatic process where the pressure and the temperature increases and the volume decreases. Between station 3 and 4 the combustion takes place, heat is added and the volume and the entropy increases and the temperature reaches its peak. Between station 4 and 5 is the turbine, where the pressure and the temperature decreases and the volume increases while the air flows through the turbine, converting heat to mechanical work. Finally, between 5 and 6, the air goes through a nozzle back to ambient pressure, while accelerating. To describe the flow and thermodynamic properties a number of approximations and idealizations are made. We assume frictionless and inviscous flow to avoid fluid losses. We use the equation of state for ideal gas: p/ρ = RT . These equations offer results that can be used for a qualitative overview and preliminary design decisions. Figure 4: TS diagram of the ideal Brayton Cycle for Turbojet The ideal open Brayton cycle consists of 4 processes, isentropic compression, isobaric heat addition and isentropic expansion and then an isobaric heat rejection between exit and inlet. We can see these relationships: Work done by compressor: EW,c = m ̇a(h03 − h02) (3) 8

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