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| F100 | |
|---|---|
 |
|
| F100 for an F-15 Eagle being tested | |
| Type | Turbofan |
| National origin | United States |
| Manufacturer | Pratt & Whitney |
| First run | 1970s |
| Major applications | F-15 Eagle F-15E Strike Eagle F-16 Fighting Falcon Northrop Grumman X-47B |
| Developed into | Pratt & Whitney PW1120 |
Contents
Development
In 1967, the United States Navy and United States Air Force issued a joint engine Request for Proposals (RFP) for the F-14 Tomcat and F-15 Eagle fighters. The combined program was called Advanced Turbine Engine Gas Generator (ATEGG) with goals to improve thrust and reduce weight to achieve a thrust-to-weight ratio of 9. The program requested proposals and would award Pratt & Whitney a contract in 1970 to produce F100-PW-100 (USAF) and F401-PW-400 (USN) engines. The Navy would cut back and later cancel its order, choosing to continue to use the Pratt & Whitney TF30 engine from the F-111 in its F-14.[2]Variants
F100-PW-100
F100-PW-200
The F-16 Fighting Falcon entered service with the F100-200, with only slight differences from the -100. Seeking a way to drive unit costs down, the USAF implemented the Alternative Fighter Engine (AFE) program in 1984, under which the engine contract would be awarded through competition. The F-16C/D Block 30/32s were the first to be built with the common engine bay, able to accept the existing engine or the General Electric F110.F100-PW-220/220E
The F100-PW-220 incorporated the most advanced technology available, including the precision control and advanced maintenance features of digital electronic controls and the extended durability and reliability of metallurgical and heat-transfer advances. The F100-220 was introduced in 1986 and could be installed on either an F-15 or F-16.[citation needed] A non-afterburning variant, the F100-PW-220U powers the Northrop Grumman X-47B UCAV. The "E" abbreviation from 220E is for equivalent. The abbreviation is given to engines which have been upgraded from series 200 to 220, thus becoming equivalent to 220 specifications.F100-PW-229
Using technology developed from the F119 and F135 engine programs for the F-22 Raptor and F-35 Lightning II,[citation needed] the current production F100-PW-229 incorporates modern turbine materials, cooling management techniques, compressor aerodynamics, and electronic controls. The first -229 was flown in 1989 and has a thrust of 17,800 lbs (dry thrust) and 29,160 lbs with afterburner. It currently powers late model F-16s and the F-15E Strike Eagle.Applications
- F100
- McDonnell Douglas F-15 Eagle
- McDonnell Douglas F-15E Strike Eagle
- General Dynamics F-16 Fighting Falcon
- Northrop Grumman X-47B
- F401
- Grumman F-14B Tomcat (planned; test aircraft only)
- Rockwell XFV-12
- Vought Model 1600 (proposed)
Specifications (F100-PW-229)
Data from [4]
General characteristics
- Type: Afterburning turbofan
- Length: 191 in (4,851 mm)
- Diameter: 34.8 in (884 mm) inlet, 46.5 in (1,181 mm) maximum external
- Dry weight: 3,740 lb (1,696 kg)
Components
- Compressor: Dual Spool Axial compressor with 3 fan and 10 compressor stages
- Bypass ratio: 0.36:1
- Combustors: annular
- Turbine: 2 low-pressure and 2 high-pressure stages
Performance
- Maximum thrust: 17,800 lbf (79.1 kN) military thrust, 29,160 lbf (129.6 kN) with afterburner
- Overall pressure ratio: 32:1
- Turbine inlet temperature: 2,460 °F (1,349 °C)[5]
- Specific fuel consumption: Military thrust: 0.76 lb/(lbf·h) (77.5 kg/(kN·h)) Full afterburner: 1.94 lb/(lbf·h) (197.8 kg/(kN·h))
- Thrust-to-weight ratio: 7.8:1
See also
- Related development
- Comparable engines
- Related lists
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