General Electric TF39

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TF39
ILA 2008 PD 083.JPG
A TF39 on a C-5 Galaxy at ILA (Internationale LuftfahrtAusstellung) in Berlin, 2008
Type Turbofan
Manufacturer GE Aviation
First run 1964
Major applications Lockheed C-5 Galaxy
Variants General Electric CF6
Developed into General Electric LM2500

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 of engines, and formed the basis of the General Electric LM2500 marine and industrial gas turbine.

Development[edit]

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, Lockheed's aircraft and General Electric's engine were selected for the new design in 1965.

The high-bypass turbofan was a huge leap in engine performance, offering a 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[edit]

TF39s on a C-5 Galaxy, from the rear

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 is snubbered ('Snubbers' are protuberances that stick-out at right angles to the fan aerofoil somewhere between mid-span and blade tip). The snubbers on adjacent fan blades butt-up against each other, in a peripheral sense and improve the vibration characteristics of the blade to the fan rotor which has a set of inlet guide vanes for the outer bypass section and the core booster stage located in front of the fan rotor, rather than behind. This unique design is clearly seen from the front.[2][3]

Applications[edit]

  • Lockheed C-5A/B/C Galaxy

Specifications (TF39-1C)[edit]

Data from [4]

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[edit]

Related development
Comparable engines
Related lists

References[edit]

  1. ^ General Electric - CF6 history
  2. ^ www.planes.cz - TF39 front view
  3. ^ www.airliners.net - TF39 running
  4. ^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 119
  • 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[edit]