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Microturbo TRS 18

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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

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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

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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

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

Manned

Unmanned

Specifications (TRS 18-046)

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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

References

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  1. ^ "Turbine engines of the World - Microturbo". Flight. Vol. 105, no. 3383. 10 January 1974. p. 49.
  2. ^ 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.