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Syllabus |
Operating cycle of a jet engine. Ideal behaviour of components. Effect of firing at a finite Mach number. Turbojet with afterburner. Turbofan with separate exhaust flows. Turbo¬fan mixed with exhaust flows. Mixer ideal constant pressure. Turbofan ideal to afterburner
Performance of gas turbine components. Propulsion equation. Specific fuel consumption. Maximum thrust. Calculation with average values. Gas turbine components: intake, compressor, combustor, turbine and propelling nozzle
Actual cycle of a gas turbine engine. Turbojet, turbofan, turbo¬propeller, turbo¬shaft
Off design performance of turbojet, turbofan, turbo¬propeller and turbo¬shaft engines. Characteristic curves of components
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Main Bibliography |
El-Sayed, Ahmed, Aircraft Propulsion and Gas Turbine Engines, CRC Press. Saravanamuttoo, H.; Rogers, G.; Cohen, H.; Straznicky, P.; Gas Turbine Theory, Prentice Hall. Oates, G. C., Aerothermodynamics of Gas Turbine and Rocket Propulsion, AIAA.
Oates, G. C. (Ed.), Aerothermodynamics of Aircraft Engine Components, AIAA.
The Jet Engine, The Technical Publications Department, Rolls-Royce plc.
Mattingly, J. D., Heiser, W. H., Daley, D. H., Aircraft Engine Design, AIAA.
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