Microturbo TRI-40
{{short description|Turbojet engine for missiles and UAVs}}
| {{Infobox aircraft begin
| name=TRI-40 | image= | caption= }}{{Infobox Aircraft Engine |type=Single Spool Turbojet |manufacturer=Microturbo |national origin=France |major applications=Kongsberg Naval Strike Missile |produced= |number built= |program cost= |developed from=Microturbo TRI 60 |variants with their own articles= }} |
The Microturbo TRI-40 is a small turbojet engine developed for use in cruise missiles and small unmanned aerial vehicles in the 2.2 - 3.6 kN (500 - 800 lbf) thrust class.
Development and Design
The TRI-40 engine is a modified version of the Microturbo TRI 60 class of small turbojets, designed to be smaller and lighter for new missiles. It is currently being used on the Kongsberg Naval Strike Missile (NSM) for the Royal Norwegian Navy and the updated MM-40 Exocet Block 3 anti-ship missile.Microturbo TRI 40/TRI 60 (2008). The Market for Missile/Drone/UAV Gas Turbine Engines. [http://www.forecastinternational.com/samples/F655_CompleteSample.pdf Forecast International]. Accessed 20 Oct 2009.
There are several differences between the TRI-40 and the older TRI-60 engines. One is that the -40 uses a 4-stage compressor rather than the 3 stage compressor that the original TRI-60 models use (although several newer variants of the TRI-60 use a 4-stage compressor as well). Another major difference is that the bearing system is lubricated by fuel rather than a separate oil system. Finally, the engine is much more "electric" than the TRI-60. It has a permanent magnet based generator (270 V DC) mounted directly on the engine shaft, which older engines lacked, as well as an ECU controlled fuel metering system.RIDEAU, Jean-François, GUYADER, Gilles, CLOAREC, Alain (2008). MICROTURBO Families of Turbojet Engine for Missiles and UAV’s From the TR60 to the new bypass turbojet engine generation. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 21–23 July 2008, Hartford, CT. AIAA 2008-4590.
Specifications (TRI-40)
{{jetspecs
|ref=[http://www.microturbo.fr/article.php3?id_article=175&lang=en TRI-40] {{webarchive|url=https://web.archive.org/web/20081114020116/http://www.microturbo.fr/article.php3?id_article=175&lang=en |date=2008-11-14 }}. Microturbo Website. Accessed 20 Oct 2009.
|type=single-spool turbojet
|length=680 mm (26.77 in)
|diameter=280 mm (11.02 in)
|weight=44 kg (97 lb)
|compressor=4 stage axial
|combustion=annular
|turbine=single-stage
|fueltype=JP-8, JP-10 (fuel)
|oilsystem=
|power=
|thrust=2.5-3.3 kN (560-750 lbf)
|compression=
|bypass=
|aircon=
|turbinetemp=1010 °C (1850 °F)
|fuelcon=
|specfuelcon= < 32.7 mg/Ns (<2.65 lb/hr*lb)
|power/weight=
|thrust/weight=5.7 - 7.3
}}
See also
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|related=
|similar engines=
|lists=
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