A model jet engine construction and using different liquid fuels

The aim of this study was to design and manufacture a model jet engine. To build the engine, Brayton cycle in theory and aircraft turbojet engines in practice were referred. As the compressor-turbine section of the model, a turbocharger, which was built for a diesel engine, was selected and adopted. During the experiment, turbine inlet temperature was between 1165 and 1454 K. However, temperature of the turbine outlet and exhaust nozzle temperatures were between 911 and 975 K. When the fuel pressure was around 700 kPa and compressor inlet pressure of 600 kPa, inlet temperature was 1165 K, combustion chamber inlet temperature was 278 K, manometric pressure was 39 kPa and the exhaust nozzle temperature was 975 K. When the fuel pressure was around 700 kPa and compressor inlet pressure of 1200 kPa, inlet temperature was 1454 K, combustion chamber inlet temperature was 291 K, manometric pressure was 39 kPa and the exhaust nozzle temperature was 911 K. Measured thrust values of the model jet engine were between 11 and 18,3 N.