Abstract: Jet engines are required to operate at a higher rpm for the same thrust values in cases such as aircraft landing and military loitering. High rpm reflects higher efficiency with increased pressure ratio. Turbofan Power Ratio, which is a compound thermodynamic value of various pressures and temperatures across the engine, is proportional to the thrust output of the turbofan, and the same relationship was proven by the author earlier regarding turbojet engines with fixed geometry exhaust nozzle. This work provides the review on performance parameters related to turbojet engine. All simulations will be done on MATLAB Tool.

Keywords: Jet Engine, Energy Efficiency, Engine Pressure, Exhaust Nozzle etc.

PDF | DOI: 10.17148/IJARCCE.2022.114210

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