| 释义 |
- Design and development
- Variants
- Applications
- Specifications (TRS 18-046)
- References
| name=TRS 18 | image= | caption= }}{{Infobox Aircraft Engine | type=Turbojet | manufacturer=Microturbo SA | designer= | national origin=France | first run= | major applications= | produced= | number built= | program cost= | unit cost= | developed from= | variants with their own articles=
}} |
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 developmentThe 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. It gained its US Federal Aviation Administration type certificate in May 1976. VariantsData from Jane's All the World's Aircraft 1984-85- 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).
ApplicationsData from Jane's All the World's Aircraft 1984-85[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 (TRS 18-046) {{jetspecs
|ref=Jane's All the World's Aircraft 1984-85
|type=Single shaft centrifugal turbojet.
|length=650 mm (25.59 in)
|diameter=325 mm (12.80 in) wide × 350 mm (13.78 in) high.
|weight=37 kg (81.6 lb) dry, basic, no jet pipe.
|compressor=Centrifugal; one piece with diffuser and straightener vanes.
|combustion=Folded, with ten spill type burners.
|turbine=Axial.
|fueltype=Electric pump.
|oilsystem=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.
|power=
|thrust=Take-off 1.10 kN (247 lb st). Maximum continuous 1.00 kN (225 lb st).
|compression=
|aircon=
|turbinetemp=
|fuelcon=
|specfuelcon=35 g/(kN⋅s) (1.24 lb/h⋅lb st).
|thrust/weight=3.0
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}}References1. ^1 {{cite magazine |last= |first= |authorlink= |coauthors= |date=10 January 1974 |title=Turbine engines of the World - Microturbo|magazine= Flight|volume=105 |issue=3383 |page=49 |id= |url= http://www.flightglobal.com/pdfarchive/view/1974/1974%20-%200053.html |accessdate= |quote= }}
}}{{Microturbo aeroengines}} 2 : Turbojet engines 1970–1979|Centrifugal-flow turbojet engines |