The Turbomeca Marboré is a small turbojet engine that was produced by Turbomeca from the 1950s into the 1970s. The most popular uses of this engine were in the Fouga CM.170 Magister and the Morane-Saulnier MS.760 Paris. It was also licensed for production in the United States as the Teledyne CAE J69.
|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 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 kg (310 lb). Fuel consumption is 720 L/h (160 imp gal/h; 190 gal/h) on the Marboré VI at 4,500 m (14,800 ft), as compared to 520 L/h (110 imp gal/h; 140 gal/h) on Marboré II engines (same altitude). An increase of 27% fuel consumption and a decrease in cruise range capabilities.
- Marboré I
- Prototypes and test examples
- Marboré II
- The first major production version was the Marboré II, which had a maximum thrust of 3.9 kN (880 lbf) at 22,500 rpm. In its most basic form, it is a single-spool, centrifugal compressor turbojet. Fuel consumption was rated at 410 L/h (90 imp gal/h; 110 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 differ depending on the variant, auxiliary components and mounting configurations.
- Marboré IIC
- Marboré III
- Marboré IV
- Marboré V
- Marboré VI
- The Marboré VI series were slightly more powerful at 4.8 kN (1,100 lbf) instead of 3.9 kN (880 lbf). Fuel consumption was only slightly higher at 450 L/h (99 imp gal/h; 120 gal/h). This was a 23% increase in thrust with slightly more than a 9% increase in fuel consumption. As a result, the VI series were used to re-engine many II-series powered aircraft, and Marboré II engines became available at discount prices.
- Teledyne CAE J69: Licence production and development in the United States.
- Ambrosini Sagittario
- Bölkow Bo 46
- Fouga CM.170 Magister
- Fouga CM.175 Zéphyr
- Hispano HA-200
- Miles Student
- Morane-Saulnier MS.755 Fleuret
- Morane-Saulnier MS.760 Paris
- Nord Aviation CT20
- SNCASO Deltaviex
- SNCASO Trident
- Stargate YT-33
- See Teledyne CAE J69
Specifications (Marboré II)Edit
- Type: Turbojet
- Length: 1,064 mm (41.9 in)
- Diameter: 567 mm (22.3 in)
- Dry weight: 133 kg (293 lb)
- Compressor: Single-stage centrifugal
- Combustors: Annular combustion chamber
- Turbine: Single-stage axial flow
- Fuel type: Aviation kerosene Air 3405 (JP-1)
- Oil system: Dry sump, Turbomeca gear pump at 4.8 bar (70 psi)
- Maximum thrust:
- Take-off:3.9 kN (880 lbf) at 22,600 rpm / sea level
- Max continuous:3.14 kN (705 lbf) at 21,000 rpm / sea level
- Overall pressure ratio: 4:1
- Air mass flow: 7.6 kg (17 lb)
- Turbine inlet temperature:
- Before turbine:800 °C (1,470 °F; 1,070 K)
- After turbine:610 °C (1,130 °F; 883 K)
- 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
- Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 164–165.