Microturbo TRS 18
| TRS 18 | |
|---|---|
| |
| Type | Turbojet |
| National origin | France |
| Manufacturer | Microturbo SA |
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.
Design and development[edit]
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]
Variants[edit]
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).
Applications[edit]
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
Specifications (TRS 18-046)[edit]
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
References[edit]
- ^ "Turbine engines of the World - Microturbo". Flight. Vol. 105, no. 3383. 10 January 1974. p. 49.
- ^ a b c d e Taylor, John W. R. (1984). Jane's All the World's Aircraft 1984-1985. London: Jane's Publishing Co. p. 811. ISBN 0710608012.