Turbojet Design Project

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Thermodynamic design of a Turbojet engine for the given conditions of altitude and speed. Blade geometry was taken into consideration for this project. A Matlab program was written to calculate the best compressor ratio, temperatures and geometry to obtain maximum thrust. Inlet and Nozzle were drafted using CREO Parametric.

Transcript of Turbojet Design Project

Training Program for Infotech Aerospace Services

Turbojet DesignCarlos J Gutirrez Romn Ramn Natal Ramos 54543 70286ME4935 Aircraft PropulsionOctober 31, 2013

1Problem Definition2Design a turbojet engine under the following conditions:Altitude of 37000 ft.The pressure ratio across the compressor c.The Mach number M0=2.0.Maximum enthalpy ratio =7.0Fuel type is hydrocarbon with QR = 42800 kJ/kg

For a range of compressor pressure ratios, namely 2