General Electric TF39
The General Electric TF39 is a high-bypass turbofan engine. Developed to power the Lockheed C-5 Galaxy, it was the first high-power high-bypass jet engine available. The TF39 was developed into the CF6 series engines, and formed the basis of the General Electric LM2500 marine and industrial gas turbine.
Development
The United States Air Force opened the "CX-X Program" in 1964, intending to produce a next-generation strategic airlifter. Of the several airframe and engine proposals returned for consideration, in 1965 Lockheed's aircraft design and General Electric's engine design were selected for the new design.
The high-bypass turbofan was a huge leap in engine performance, offering high thrust of 43,000 pounds, while improving fuel efficiency by about 25%.[1] The TF39 had an 8-to-1 bypass ratio, 25-to-1 compressor pressure ratio, a 2,500 °F (1,370 °C) turbine temperature made possible by advanced forced-air cooling. The first engine went for testing in 1965. Between 1968 and 1971, 463 TF39-1 and -1A engines were produced and delivered to power the C-5A fleet.
Design
The TF39 is a revolutionary 1960s engine rated from 41,000 to 43,000 lbf (191 to 205 kN) of thrust. It employed a great deal of then-new technological features such as:
- 1½ stage fan blades (unique to TF39).
- 8:1 bypass ratio.
- Variable stator vanes.
- Turbines equipped with advanced cooling.
- Fuel efficiency better than any engines available at the time.
- Cascade-type thrust reversers.
Mechanically, the TF39 is rather unusual for a high bypass ratio turbofan; the single stage snubbered[2] fan rotor has a set of inlet guide vanes for the outer bypass section and the core booster stage is located in front of the fan rotor, rather than behind. This unique design is clearly seen in front view.[3][4]
Applications
Specifications (TF39-1C)
Data from [5]
General characteristics
- Type: Turbofan
- Length: 312 in (792 cm)
- Diameter: 97 in (246 cm)
- Dry weight: 8000 lb (3630 kg)
Components
- Compressor: Axial, 1 stage fan, 5 stage low pressure compressor, 16 stage high pressure compressor
- Combustors: Annular
- Turbine: Axial, 2 stage high pressure turbine, 6 stage low pressure turbine.
Performance
See also
- Related development
- Comparable engines
- Related lists
References
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
External links
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