AMT Netherlands designs and manufactures small gas turbines for the propulsion of :
- target drones,
- radio-controlled flying aircraft,
- experimental aircraft development,
- full size gliders.
The original Olympus design was redesigned in 2004 to the HP version, in 2010 the engine is converted to a direct kerosene starting system.
The engine is highly used in the "model jet scene" but also professionals are using the Olympus HP. A spinoff of the Olympus HP is being certified by EASA for the use as a "bringing home device" for a full size glider. For universities a "special" layout is available with measuring points.
The Olympus engine has been constructed from a single radial compressor and an axial turbine.
AMT Olympus Technical data
|Diameter||130 mm||5.1 in.|
|Lenth||374 mm||14.7 in.|
|Not equipped||2900 g||6.4 lbs|
|Equipped||3845 g||8.5 lbs|
|Max RPM||108 500 t/mn||108,500 rpm|
|Thrust at max||230 N||51.7 lb|
|Thrust at idle||13 N||2.9 lb|
|Pressure ratio at max||3,8 / 1|
|Max flow||450 g/s||0.99 lbs/sec|
|Max continue EGT||750 deg.C||1380 def.F|
|Fuel Consumption||640 gr/min||22.5 oz/min|
|Specific fuel consumtion||46.4 gr(KN*sec)||1.64 lb(lb*hr)|
The time required for the turbine to spool up and down is influenced by the low mass of its axial turbine Wheel :
- from min. RPM to max. RPM in less than 4 seconds
- from max. RPM to min. RPM in less than 2 seconds.
The combustion chamber is of the annular type, which is provided with a unique low pressure fuel system, developed by AMT.
From this same fuel system both hybrid bearings are also lubricated. A separate oil supply for lubrication is therefore no longer necessary.
The turbine is protected by means of a microprocessor controller (ECU) that regulates the maximum turbine performance within the software limits. The ECU is fully automatic and needs no adjustment