|CFE738 on a Dassault Falcon 2000|
|National origin||United States|
|First run||May 1990|
|Major applications||Dassault Falcon 2000|
|Developed from||General Electric GE27|
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).
Chosen to power the Falcon 2000 in 1990, the engine was also first run in May 1990, and it was first flown on a Boeing 727 testbed on 31 August 1992. The CFE738-1 made its inaugural flight on a Falcon 2000 prototype on March 4, 1993. It was certified by the United States Federal Aviation Administration (FAA) on December 17, 1993, and it entered service in 1994.
Data from Élodie Roux (2007), pp.125-126: 125–126