|Marboré II on display at the Museum für Luftfahrt und Technik|
|First run||16 June 1951 (first flight)|
|Major applications||Fouga Magister
|Variants||Teledyne CAE J69|
The Turboméca Marboré was a small turbojet engine produced by Turbomeca from the 1950s into the 1970s. The most popular uses of this engine were in the Fouga Magister and the Morane-Saulnier MS-760. It was also licensed for production in the United States as the Teledyne CAE J69,.
The first major production version was the Marboré II, which had a maximum thrust of 880 lbf (3.9 kN) at 22,500 rpm. In its most basic form, it is a single-spool, centrifugal compressor turbojet. Fuel consumption was rated at 109 gal/h. Variations include military or civilian aircraft, oil tank design, auxiliary equipment, and exhaust pipe configuration. Some variants also included one axial stage compressor for additional performance. The engine dimensions of different variants with different auxiliary components and mounting configurations.
These were eventually replaced by the Marboré VI series which were slightly more powerful at was 1080 lbf (4.8 kN) instead of 880 lbf. Fuel consumption was only slightly higher at 119 gal/h. This was a 23% increase in thrust with slightly more than a 9% increase in fuel consumption. As a result the IV series were used to re-engine many II-series aircraft, and Marboré II engines are still available cheaply as surplus for the experimenter.
The original Marboré, as well as Marboré III, IV, and V were not produced in significant numbers.
A typical weight for this series of engines is 140 kilograms or 310 pounds.
Fuel consumption is 190 gallons per hour on the Marbore VI at 15,000 feet, as compared to 138 gallons per hour on Marbore II engines (same altitude). An increase of 27% fuel consumption and a decrease in cruise range capabilities.
- Marboré I
- Marboré II
- Marboré IIC
- Marboré III
- Marboré IV
- Marboré V
- Marboré VI
- Teledyne CAE J69:Licence production and development in the United States.
- Ambrosini Sagittario
- Bölkow Bo 46
- Fouga Magister
- Fouga Zéphyr
- Hispano HA-200
- Morane-Saulnier MS.755 Fleuret
- Morane-Saulnier MS.760 Paris
- Nord Aviation CT20
- SNCASO Trident
- See Teledyne CAE J69
Specifications (Marboré IIC)
Data from FAA TCDS
- Type: Turbojet
- Length: 61.7 in (156.7 cm)
- Diameter: 24.9 in (63.2 cm)
- Dry weight: 358 lb (162.4 kg)
- Compressor: Single stage centrifugal
- Combustors: Single annular combustion chamber
- Turbine: Single stage
- Fuel type: Aviation kerosene Air 3405 (JP-1)
- Maximum thrust: 880 lbf (3.91 kN) at 22,600 rpm
- Turbine inlet temperature: 650 C
- Thrust-to-weight ratio: 2.458 lbf/lb (0.024 kN/kg)
- Related development
- Related lists
- Gunston 1989, p.169.
- CM-170 Flight Tests, Airplane Cruise Performance Charts, and Aircraft Flight Manuals
- FAA Type Certificate Data Sheet Retrieved: 2 November 2008
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
|Wikimedia Commons has media related to Turbomeca Marboré.|
- Iconic's Marbore IIC
- Aircraft fitted with MARBORE II or VI
- minijets website Marboré I
- Minijets website Marboré II / IV