When modifying the system, safety was to be the primary concern. The engine was required to be safely operable in a laboratory setting. The engine was also required to be more reliable and robust in its operation. The engine was to be outfitted with sensors such that relevant data could be obtained in order to perform a laboratory experiment and thus reinforce the lessons of several different courses.


The main components of a typical turbojet engine are a diffuser, compressor, combustion chamber, turbine, and nozzle. The engine described in this report contains all of these components except the diffuser, which is unnecessary because the engine is stationary. The compressor and turbine are part of a Garrett turbocharger. The combustion chamber and nozzle were constructed by the team. Air enters the system through the inlet of the turbocharger. It flows through the compressor and into the combustion chamber where propane fuel is added and ignited. This mixture then flows through the turbine side of the turbocharger and exits through the nozzle. The engine is started by spinning up the turbocharger with compressed air, then turning on a spark and providing fuel. Once the engine is started the spark is turned off.  The engine will continue to run as long as fuel is provided. 


The main components of the original engine were a compressor, combustion chamber, and turbine. The compressor and turbine were part of a Garrett turbocharger.  The engine operated in a similar manner but was started by holding a leaf blower against the turbocharger inlet. Other engine components included an ignition coil, oil pump, an oil pressure gauge mounted on the compressor housing, a water pump, a radiator for water cooling, and a control panel. Power was supplied to the pumps and ignition coil by a 12V battery. The control panel had three switches for starting the oil pump, water pump, and spark. 






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