Turbomeca Marboré - Misplaced Pages

(Redirected from Turbomeca Marbore)

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. In Spain the Turbomeca model Marboré II was manufactured by ENMASA under license with the name Marboré M21.

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.

Variants

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 lb_f) 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
Marboré IIB
Marboré IIC
Marboré IIF
Marboré IIG
Marboré III
Marboré IV
Marboré V
Marboré VI: The Marboré VI series were slightly more powerful at 4.8 kN (1,100 lb_f) instead of 3.9 kN (880 lb_f). 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
Marboré VIF

Applications

Marboré

J69: See Teledyne CAE J69

Specifications (Marboré II)

Data from FAA TCDS, Aircraft engines of the World 1953

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

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)

Specific fuel consumption: 110 kg/kN/h (1.08 lb/lbf/h)
Thrust-to-weight ratio: 3.03

References

Gunston 1989, p.169.
CM-170 Flight Tests, Airplane Cruise Performance Charts, and Aircraft Flight Manuals
^ Wilkinson, Paul H. (1964). Aircraft engines of the World 1964-65 (20th ed.). Washington D.C.: Paul H. Wilkinson. p. 168.
FAA Type Certificate Data Sheet Archived 2016-12-28 at the Wayback Machine 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.