Microturbo TRS-18 Turbojet

microjet-18


The Microturbo TRS 18 is a small, low thrust turbojet designed and built in France in the 1970s. It was installed on both manned and unmanned aircraft.

The TRS 18 was originally designed for self-launching motor gliders but was adapted to power conventional ultralight aircraft and unmanned vehicles (RPV). It was originally designed and developed by Sermel, a competitor company to Microturbo which the latter took over in 1971. It is a simple, low thrust, reverse flow single shaft engine with a centrifugal compressor and axial turbine. It is built in three modules: an intake section containing starter and lubrication systems; a centre section with compressor and turbine on ball bearings; and an aft section with the folded combustion chambers and tail-pipe.

 

Micro-TRS-18-3

 

Early microjets developed 200 lbs thrust, while the newer TRS 18-1 engine develops 325 lbs thrust with nearly identical in dimension & weight.  

It gained its US Federal Aviation Administration type certificate E13CE on 25 May 1976.

 

Micro-TRS-18-046
TRS 18-046

 

Variants

TRS 18-046
Production version, primarily intended for manned applications with full self start provision, oil lubrication and temperature and pressure transducers.

TRS 18-056
Cut down gas generator or core engine version, fuel lubricated and only 62% the weight of the 18-046 version but the same thrust; intended for RPVs.

TRS 18-075
Intended respectively for the Flight Refuelling ASAT target drone. Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046. Take-off thrust increased to 1.15 kN (260 lb st) and maximum continuous thrust to 1.10 kN (247 lb st).

TRS 18-076
Intended for the Meteor-Mirach 100. Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046. Take-off thrust increased to 1.15 kN (260 lb st) and maximum continuous thrust to 1.10 kN (247 lb st).

Applications:

Manned

Bede BD-5J
Caproni Vizzola A-21SJ
Chagnes Microstar (version of Rutan VariViggen)
EFF Prometheus 19
EFF Prometheus 12
Microjet 200
NASA AD-1 slew wing

Unmanned

Flight Refuelling ASAT
France-engins Mitsoubac
Meteor-Mirach 100

Specifications:

 

Microturbo TRS 18-1
Thrust: 325 lbs
Max Running Altitude: 30,000 ft.
Weight: 84.88 lb
Length: 27 in
Diameter: 13 in. 
Fuel Types: Jet A, JP4-JP5
Oil Types: MIL-L-23699 
Fuel Consumption (Max Power): 283 lbs./hr. 

 

TRS 18-046

Type: Single shaft centrifugal turbojet.
Length: 650 mm (25.59 in)
Diameter: 325 mm (12.80 in) wide × 350 mm (13.78 in) high.
Dry weight: 37 kg (81.6 lb) dry, basic, no jet pipe.
Compressor: Centifugal; one piece with diffuser and straightener vanes.
Combustors: Folded, with ten spill type burners.
Turbine: Axial.
Fuel type: Electric pump.
Oil system: Submerged pump in tank on front underside; filter and pressure transducer on upper side. Closed circuit with high pressure supply to rotor and gearbox bearings.
Maximum thrust: Take-off 1.10 kN (247 lb st).
Maximum continuous 1.00 kN (225 lb st).
Specific fuel consumption: 35 mg/N/s (1.24 lb/h/lb st).
Maximum altitude: 9000 m