Marboré
Marboré on display at the Air Corps Museum, Baldonnel, Dublin
Type Turbojet
National origin France
Manufacturer Turbomeca
First run 16 June 1951 (first flight)
Major applications Fouga Magister
Fouga Zéphyr
Variants Teledyne CAE J69

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.[1]

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), as well as an increase of fuel consumption of 27% and a decrease in cruise range capabilities.[2]

Variants

Marboré II displayed at 1953 Paris Air Show
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 IIA
[3]
Marboré IIB
[3]
Marboré IIC
[3]
Marboré IIF
[3]
Marboré IIG
[3]
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.
Marboré VIC
[3]
Marboré VIF
[3]

Applications

Two Marboré engines powered the Hispano HA-200
Marboré
J69
See Teledyne CAE J69

Specifications (Marboré II)

Sectioned Marboré II on display at the Finnish Airforce Museum

Data from FAA TCDS,[4] Aircraft engines of the World 1953[5]

General characteristics

  • Type: Turbojet
  • Length: 1,064 mm (41.9 in)
  • Diameter: 567 mm (22.3 in)
  • Dry weight: 133 kg (293 lb)

Components

  • 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)

Performance

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
Before turbine: 800 °C (1,470 °F; 1,070 K)
After turbine: 610 °C (1,130 °F; 883 K)

See also

Related development

Related lists

References

  1. ↑ Gunston 1989, p.169.
  2. ↑ CM-170 Flight Tests, Airplane Cruise Performance Charts, and Aircraft Flight Manuals
  3. 1 2 3 4 5 6 7 Wilkinson, Paul H. (1964). Aircraft engines of the World 1964-65 (20th ed.). Washington D.C.: Paul H. Wilkinson. p. 168.
  4. ↑ FAA Type Certificate Data Sheet Retrieved: 2 November 2008
  5. ↑ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 164–165.
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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