The engine is a small turbo jet engine and modified for educational purposes. The unit has a radial flow compressor and an axial flow turbine as in modern jet plane.
Inlet air through an orifice flow measuring device is compressed by a single stage radial flow compressor. The turbine is motor started and runs on Jet A fuel. Fuel is injected and ignited in the combustion chamber providing hot gas for a single stage axial flow turbine which inturn drives the compressor. The gas is exhausted through a nozzle at high velocity providing a thrust. The turbine runs on ceramic bearings. Lubrication is provided by jet oil in the fuel, and no separate lubrication system is required. A fan is provided for engine cooling.
An Electronic Control Unit (ECU) controls the basic turbine operation. Additional instruments are provided for monitoring and controlling engine operation and performance.
A touch screen computer with an interface unit, and software are provided for speed control, data display and analysis, and to assist the ECU.
A transparent engine cover and over speed shutdown are provided.
Instruction manual is also included.
|– Diffuser||High strength aluminium.|
|– Combustion chamber||Stainless steel.|
|– Turbine||Vacuum cast inconel.|
|– Compressor||High grade aluminium alloy.|
|Engine performance specifications.|
|– Maximum static thrust||Up to 70 N at approx. 150,000 rpm.|
|– Starting and running fuel||Jet A or Kerosene with jet oil.|
|– Temperatures||Inlet air, diffuser exit, turbine guide vane entry and exit and nozzle exit.|
|– Pressures||Diffuser exit and turbine exit.|
|– Fuel flow rate.|
|– Air flow rate||Differential pressure at inlet orifice.|
|Power supply||220V, 1 Ph, 50Hz. Other power supply is available on request.|