General Electric CFE738

The General Electric CFE738 is a small turbofan engine aimed at the business/commuter jet market, and is used on the Dassault Falcon 2000.

Design

The CFE738 is comprised 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 240lb/s. The take-off thrust is 5600lbf, flat-rated to ISA+15C.

Derivatives

In the late 1980s, GE proposed a turboprop, the "T407" or "GLC38", for the Lockheed P-7, with a maximum takeoff power of 4,475 kW (6,000 SHP). The CFE738 is based on this engine. [http://www.faqs.org/docs/air/v2003m10.html Greg Goebel's "Vectors"] ]

The derivative GE38-1B (7,500 shp) is slated to power the new Sikorsky CH-53K three-engined helicopter for the USMC. [ [http://www.defense-aerospace.com/cgi-bin/client/modele.pl?prod=78346&session=dae.24505520.1170350647.RcIiN8Oa9dUAAA3VhV8&modele=release GE Launches New Engine Program for U.S. Marine Corps Heavy-lift Helicopter ] ]

pecifications

*Fan/Compressor Stages: 1/5+1C
*High-Pressure Turbine/Low-Pressure Turbine Stages:: 2/3
*Fan Diameter ~in: 35.50
*Length ~in: 68.3
*Basic Engine Weight~lb: 1,214
*Dry Weight ~lb: 1,325
*Max. Thrust (Sea Level Static)~lbf: 5,918
*Specific Fuel Consumption (Sea Level Static) ~lb/hr/lbf: 0.369
*Cruise Net Thrust (Mach 0.8,40000ft,ISA) ~lbf: 1310
*Specific Fuel Consumption (Mach 0.8,40000ft,ISA)~lb/hr/lbf: 0.645
*Overall Pressure Ratio (Top-of-Climb): ~30:1
*Bypass Ratio: 5.3
*Airflow: 240lb/s

ee also

*List of aircraft engines

References

External links

* [http://geae.com/engines/corporate/cfe738.html General Electric CFE738 page] at [http://geae.com GE Aviation corporate website]