General Electric TF34
|National origin||United States|
|Major applications||A-10 Thunderbolt II |
|Variants||General Electric CF34|
Design and development
Developed by GE Aircraft Engines during the late 1960s, the original engine comprises a single stage fan, driven by a 4-stage low pressure (LP) turbine, supercharging a 14-stage high pressure (HP) compressor, driven by a 2-stage HP turbine. An annular combustor is featured. The TF34-GE-400A is rated at 9,275 lbf (41.26 kN) static thrust.
The civilian variant, the CF34, is used on a number of business and regional jets.
Initial variant for Lockheed S-3, entered production in August 1972.
Variant for Fairchild A-10A, first flown in A-10 during May 1972. Production began in October 1974.
Improved version of GE-2 for Lockheed S-3.
- Fairchild Republic A-10 Thunderbolt II
- Lockheed S-3 Viking
- Lockheed Martin RQ-170 Sentinel
- Sikorsky S-72
Data from Jane's.
- Type: Twin-shaft, high-bypass turbofan engine
- Length: 100 in (250 cm)
- Diameter: 52.2 in (133 cm)
- Dry weight: 1,478 lb (670 kg)
- Compressor: Single-stage fan, 14 stage HP axial compressor
- Combustors: Axial, annular
- Turbine: 4 stage LP, 2 stage HP
- Maximum thrust: 9,275 lbf (41 kN; 4,207 kgf)
- Specific fuel consumption: 0.363 lb/(h·lbf) (10.3 mg/Ns)
- Thrust-to-weight ratio: 6.28
- Taylor 1982, p. 781.
- Taylor, John W.R. Jane's All the World's Aircraft 1982-83., London, Jane's Publishing Company Ltd, 1982. ISBN 0 7106-0748-2.
|Wikimedia Commons has media related to General Electric TF34.|