Turbomeca Marboré
From Wikipedia, the free encyclopedia
| Marboré | |
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| Marbore IIC after a driveway run | |
| 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 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,[1].
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[edit] Variants
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[vague]. 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[vague]. 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.
[edit] Applications
[edit] Specifications (Marboré IIC)
Data from:[2]
General characteristics
- Type: Turbojet
- Length: 61.7 in
- Diameter: 24.9 in
- Dry weight: 358 lb
Components
- Compressor: Single stage centrifugal
- Combustors: Single annular combustion chamber
- Turbine: Single stage
Performance
- Maximum Thrust: 880 lbf at 22,600 rpm
- Turbine inlet temperature: 650 C
- Power-to-weight ratio:
[edit] See also
Related development
Related lists
[edit] References
- ^ Gunston 1989, p.169.
- ^ 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
[edit] External links
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