|CFE738 on a Dassault Falcon 2000|
|National origin||United States|
|Major applications||Dassault Falcon 2000|
|Developed from||General Electric GE27|
Design and developmentEdit
The CFE738 is a two-shaft design, consisting of a single stage bypass fan connected via one shaft to a 3-stage low-pressure (LP) turbine at the rear of the engine; with a six-stage combination low-pressure/high-pressure (LP/HP) axial/centrifugal compressor (five axial stages and one centrifugal stage) driven by a two-stage HP turbine, between the fan and the LP turbine, on the other shaft. There is an axial combustion chamber between the compressor stages and the HP turbine. A mixer is built in to the jetpipe to mix cold bypass air with the hot exhaust gases. The engine has an overall pressure ratio of 35:1, which is extremely high for an engine with a centrifugal compressor. Other cycle parameters are a bypass ratio of 5.3 and airflow of 240 lb/s (108.9 kg/s). The take-off thrust is 5,600 lbf (24.9 kN), flat-rated to ISA +15°C (30°C, 86°F).
- Type: Two-shaft turbofan engine
- Length: 68.3 in (1,730 mm)
- Diameter: 35.50 in (902 mm) (Fan)
- Dry weight: 1,214 lb (551 kg) (Basic) Dry Weight: 1,325 lb (601 kg)
- Compressor: Fan/Compressor Stages: 1/5+1C
- Turbine: HP Turbine/LP Turbine Stages: 2/3
- Maximum thrust: Max. Thrust (Sea Level Static): 5,900 lbf (26.3 kN), Cruise Net Thrust (Mach 0.8, 40000 ft, ISA): 1,310 lbf (5.8 kN)
- Overall pressure ratio: Takeoff: 23; Cruise: 32
- Bypass ratio: 5.3
- Air mass flow: 240 lb/s (6,500 kg/min)
- Turbine inlet temperature: 2,498 °F (1,370 °C; 2,957 °R; 1,643 K)
- Specific fuel consumption: Takeoff (Sea Level Static): 0.369 lb/(lbf⋅h) (10.5 g/(kN⋅s)), Cruise (Mach 0.8 (849.9 km/h; 528.1 mph), 40000 ft, ISA): 0.645 lb/(lbf⋅h) (18.3 g/(kN⋅s))
- Power-to-weight ratio:
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
- Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.