CFE CFE738

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The CFE738 is a small turbofan engine aimed at the business/commuter jet market manufactured by the CFE Company, and is used on the Dassault Falcon 2000.

CFE738
Dassault Falcon 2000, EBACE 2018, Le Grand-Saconnex (BL7C0617).jpg
CFE738 on a Dassault Falcon 2000
Type Turbofan
National origin United States
Manufacturer CFE Company
First run 1990
Major applications Dassault Falcon 2000
Developed from General Electric GE27

Design and developmentEdit

The success of the GE27/GLC38 gas generator development of the 1980s led to the formation of the CFE Company by GE and the Garrett Engine Division of Allied Signal (now Honeywell) in 1987.

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).

The engine was first run in 1990 and first flown on a Boeing 727 testbed on 31 August 1992.[1] It was certified by the American Federal Aviation Authority on 17 December 1993.

ApplicationsEdit

SpecificationsEdit

Data from Élodie Roux (2007), pp.125-126[2]:125126

General characteristics

  • 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)

Components

  • Compressor: Fan/Compressor Stages: 1/5+1C
  • Turbine: HP Turbine/LP Turbine Stages: 2/3

Performance

  • 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:

See alsoEdit

Related development

Related lists

ReferencesEdit

  1. ^ "Turbojet Engines - The High Bypass Turbofans Part 2". Aviation World. Air-Britain. 2004. p. 132. ISSN 1742-996X.
  2. ^ Élodie Roux (2007). Turbofan and turbojet engines: Database handbook. ISBN 9782952938013. OCLC 780131647.
  • 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.

External linksEdit