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AMT Olympus

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

Initial testing
TypeCentrifugal-flow turbojet
Nb. built


Diameter130 mm5.1 in.
Lenth374 mm14.7 in.


Not equipped2900 g6.4 lbs
Equipped3845 g8.5 lbs


Max RPM108 500 t/mn108,500 rpm
Max Idle t/mnrpm
Thrust at max230 N51.7 lb
Thrust at idle13 N2.9 lb
Pressure ratio at max3,8 / 1
Max flow450 g/s0.99 lbs/sec
Max continue EGT750 deg.C1380 def.F


Fuel Consumption640 gr/min22.5 oz/min
Specific fuel consumtion46.4 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