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Turbomeca Marboré
CAREC WP-11

  Turbomeca-Marbore
Marboré II

 

The Turboméca Marboré was a small turbojet engine produced by Turbomeca from the 1950s into the 1970s. First flown on 16 June 1951, 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.  

 

Turbo-Marbore-1
Marbore I

 

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.

 

The Marbore II has a single stage centrifugal compressor with with an annular combustion chamber and single stage turbine. Starting is by an electric starter and 2 torch igniters.

 

Turbo-Marbore-2
Marbore II

 

Marbore II was fitted on the Nord 2505 (Modified Nord 2503, powered by two 1864-kW (2,500-hp) Pratt & Whitney R-2800-CB17 radial piston engines and two Turbomeca Marboré IIE auxiliary turbojets added).

 

 Turbo-Marbore-3E
Turbomeca Marboré IIE

 

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.

 

Turbo-Marbore-4
Turbomeca Marboré VI

 

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.

 

Variants:
Marboré I
Marboré II
Marboré IIC
Marboré IIE
Marboré III
Marboré IV
Marboré V
Marboré VI
Teledyne CAE J69: Licence production and development in the United States.

 

Applications:

Marboré:
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

 

Specifications:

 

Marbore I
Diameter: 60 cm / 23.4 in
Length: 138 cm / 54.2 in
Weight: 120 kg / 265 lb
 
Marbore II
Take off thrust: 880 lbs
S.F.C: 1,15 lbs/lbs/h
Maximum continuous thrust: 705 lbs
S.F.C: 1,10 lbs/lbs/h
Weight: 322 lbs

 

Marboré IIC
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)

 

Turbo-Marbore-1-ld
Marbore I
 
Turbo-Marbore-2-ld
Marbore II

 

 

 

 

 

 

 

 

 

 

 


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