|National origin||United States|
|Major applications||Dassault Falcon 2000|
|Developed from||General Electric GE27|
Design and development
The CFE738 consists of a single stage fan, driven by a 3-stage low-pressure (LP) turbine, supercharging a 5-stage high-pressure (HP) axial/centrifugal compressor driven by a 2-stage HP turbine. 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 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+15C.
The engine was first run in 1990 and first flown on a Boeing 727 testbed on 31 August 1992. It was certified by the American Federal Aviation Authority on 17 December 1993.
- Type: Turbofan
- Length: 68.3 in
- Diameter: 35.50 in (Fan)
- Dry weight: 1,214 lb (Basic) Dry Weight: 1,325 lb
- Compressor: Fan/Compressor Stages: 1/5+1C
- Turbine: High-Pressure Turbine/Low-Pressure Turbine Stages: 2/3
- Maximum thrust: Max. Thrust (Sea Level Static): 26.3 kN (5,918 lbf), Cruise Net Thrust (Mach 0.8, 40000 ft, ISA): 1310 lbf
- Overall pressure ratio: ~30:1, Bypass Ratio: 5.3
- Air mass flow: 240 lb/s
- Specific fuel consumption: (Sea Level Static): 0.369 lb/(h lbf), (Mach 0.8, 40000 ft, ISA): 0.645 lb/(h lbf)
- Power-to-weight ratio:
- Related development
- Related lists
- 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.