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Pratt and Whitney F100

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Pratt & Whitney F100

The Pratt & Whitney F100 (company designation JTF22) is an afterburning turbofan engine manufactured by Pratt & Whitney which powers the F-15 Eagle and F-16 Fighting Falcon.



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.


The F100-100 first flew in an F-15 Eagle in 1972 with a thrust of 23,930 lbf (106.4 kN). Due to the advanced nature of engine and aircraft, numerous problems were encountered in its early days of service including high wear, stalling and "hard" afterburner starts. These "hard" starts could be caused by failure of the afterburner to start or by extinguishing after start, in either case the large jets of jet fuel were lit by the engine exhaust resulting in high pressure waves causing the engine to stall. Early problems were solved in the F100-PW-220, and the engine is still in the USAF fleet to this day.


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.


Due to the unsatisfactory reliability, maintenance costs, and service life of the F100-PW-100/200, Pratt & Whitney was eventually pressured into upgrading the engine to address these issues. The resulting engine, designated F100-PW-220, almost eliminates stall-stagnations and augmenter instability as well as doubling time between depot overhauls. Reliability and maintenance costs were also drastically improved, and the engine incorporates a digital electronic engine control (DEEC). The F100-PW-220 was introduced in 1986 and could be installed on either an F-15 or F-16. 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 100 or 200 to 220, thus becoming equivalent to 220 specifications.


The first -229 was flown in 1989 and has a thrust of 17,800 lbf (79 kN) (dry thrust) and 29,160 lbf (129.7 kN) with afterburner. It currently powers late model F-16s and the F-15E Strike Eagle. Using technology developed from the F119 and F135 engine programs for the F-22 Raptor and F-35 Lightning II, the current production F100-PW-229 EEP (Engine Enhancement Package) incorporates modern turbine materials, cooling management techniques, compressor aerodynamics, and electronic controls. Deliveries of the -229EEP began in 2009.


  • General Dynamics F-16 Fighting Falcon
  • McDonnell Douglas F-15 Eagle
  • McDonnell Douglas F-15E Strike Eagle
  • Northrop Grumman X-47B
  • Vought YA-7F
  • F401
  • Grumman F-14B Tomcat (planned; test aircraft only)
  • Rockwell XFV-12
  • Vought Model 1600 (proposed)
  • F100-PW-220

    Data from ,

    General characteristics

  • Type: Afterburning turbofan
  • Length: 191 inches (490 cm)
  • Diameter: 34.8 inches (88 cm) inlet, 46.5 inches (118 cm) maximum external
  • Dry weight: 3,234 pounds (1,467 kg)
  • Components

  • Compressor: Dual Spool Axial compressor
  • Bypass ratio: 0.63:1
  • Combustors: annular
  • Performance

  • Maximum thrust: 14,590 pounds-force (64.9 kN) military thrust, 23,770 pounds-force (105.7 kN) with afterburner
  • Overall pressure ratio: 25:1
  • Specific fuel consumption: Military thrust: (0.73 lb/(lbf·h))
  • Thrust-to-weight ratio: 7.4:1
  • F100-PW-229

    Data from

    General characteristics

  • Type: Afterburning turbofan
  • Length: 191 inches (490 cm)
  • Diameter: 34.8 inches (88 cm) inlet, 46.5 inches (118 cm) maximum external
  • Dry weight: 3,740 pounds (1,700 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 pounds-force (79 kN) military thrust, 29,160 pounds-force (129.7 kN) with afterburner
  • Overall pressure ratio: 32:1
  • Turbine inlet temperature: 2,460 °F (1,350 °C)
  • 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
  • References

    Pratt & Whitney F100 Wikipedia

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