Microturbo TRS-18 Turbojet
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.
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.
Production version, primarily intended for manned applications with full self start provision, oil lubrication and temperature and pressure transducers.
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.
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).
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).
Caproni Vizzola A-21SJ
Chagnes Microstar (version of Rutan VariViggen)
EFF Prometheus 19
EFF Prometheus 12
NASA AD-1 slew wing
Flight Refuelling ASAT
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.
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.
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