Description
A small, two-shaft, gas turbine engine with radial flow compressor and axial flow turbine as in modern power generation industry. The first shaft is a hot gas generator. 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 by a fuel pump and ignited in the combustion chamber providing hot gas for a single stage axial flow turbine which intern drives the compressor. The hot gas is discharged axially to a larger power turbine on the second shaft and exhausts to atmosphere. A fan is provided for cooling the engine. Sensors and indicators for temperatures, pressures, speeds, torque, fuel flow rate, air flow rate. Optional silencer unit.
 
