General Electric F118
| F118 | |
|---|---|
| |
| An F118 engine | |
| Type | Turbofan |
| National origin | United States |
| Manufacturer | General Electric
|
| First run | 1980s |
| Major applications | Northrop Grumman B-2 Spirit
|
| Developed from | General Electric F110 |
The General Electric F118 is a non-afterburning
GE Aviation, and is derived from the General Electric F110
afterburning turbofan.
Design and development
The F118 is a non-afterburning derivative of the F110 specially developed for the
Lockheed U-2S fleet was fitted with a modified version of the F118.[1]
Variants
Applications
- Lockheed U-2S
- Northrop Grumman B-2 Spirit
Specifications (F118-100)
Data from [3]
General characteristics
- Type: Two Spool turbofan
- Length: 101 in (260 cm)
- Diameter: 46.5 in (118 cm)
- Dry weight: 3,200 lb (1,500 kg)
Components
- Compressor: Axial, 1 stage fan, 2 stage LP compressor, 9 stage HP compressor
- Combustors: Annular
- Turbine: 1 stage HP turbine, 2 stage LP turbine
Performance
- Maximum thrust: 19,000 lbf (85 kN)
- Overall pressure ratio: 35:1
- Thrust-to-weight ratio: 5.9:1
See also
Related development
Related lists
References
Notes
- ISBN 1-880588-67-6.
- ^ a b Taylor 1996, p 594
- ^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 118.
Bibliography
- Taylor, Michael J. H. (1996). Brassey's World Aircraft & Systems Directory. London, England: Brassey's. ISBN 1-85753-198-1.
External links
Wikimedia Commons has media related to General Electric F118.