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Summary
Summary
In this study, an analytical model is created to predict the performance of a micro turbojet engine and the impact of its exit area variation on the generated thrust and fuel consumption. The model is based on empirical formulas used previously with large-scale engines. The model is verified using experimental data captured from the engine during an equilibrium run at different speeds, starting from the idle value (33,000 rpm), till reaching its maximum rated speed (112,000 rpm). Also, a complete flow analysis through the nozzle is performed using the computational fluid dynamics (CFD) software ANSYS CFX 16.0.
Performance maps
Performance maps
The performance map of the radial compressor of the engine was computed using large-scale empirical formulas
The equilibrium run line of the jet engine was concluded by solving the performance maps of all components of the whole engine, and the performance shift is predicted with different nozzle
Experimental testing of the engine
Experimental testing of the engine
The engine's performance was measured experimentally at the Military Technical College - Egypt. The measured parameters were the fuel mass flow rate, engine thrust, RPM, and exhaust temperature.
Used Software
Used Software
f-Chart Engineering Equation Solver (EES) is used to solve ~270 equations to get the performance map of the engine and its components
ANSYS CFX was used to simulate the flow through the convergent exhaust nozzle
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