Microturbo TRS 18

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.[1] 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.[2]

It gained its US Federal Aviation Administration type certificate in May 1976.[2]

Data from Jane's All the World's Aircraft 1984-85[2]

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).

Data from Jane's All the World's Aircraft 1984-85[2]

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

Data from Jane's All the World's Aircraft 1984-85[2]

General characteristics

• 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.

Components

• Compressor: Centrifugal; 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.

Performance

• Maximum thrust: Take-off 1.10 kN (247 lb st). Maximum continuous 1.00 kN (225 lb st).
• Specific fuel consumption: 35 g/(kN⋅s) (1.24 lb/h⋅lb st).
• Thrust-to-weight ratio: 3.0