Williams F112 - Misplaced Pages

Small turbofan engine in the US military

F112

An F112 engine on display at the National Museum of the United States Air Force
Type	Turbofan
National origin	United States
Manufacturer	Williams International
First run	1970s
Major applications	AGM-129 ACM
Developed from	Williams F107

The Williams F112 is a small turbofan engine made by Williams International designed to power cruise missiles. It has been used as the powerplant for the AGM-129 Advanced Cruise Missile and the AGM-86B advanced cruise missile, as well as the experimental X-36 and X-50.

Design and development

Although Williams originally designed these small turbofans to power target drones while aiming for a contract in the Subsonic Cruise Armed Decoy (SCAD) program, it quickly became apparent that these were valuable tools to be used in the future to power advanced cruise missiles. Originally designated the F107-WR-14A6, then designated the F107-WR-103 by Williams then designated the F112-WR-100 by the USAF.

Though the true benefits that the F112 brought to the AGM-129 are classified, it has been said that the F112 increased the range of the AGM-129 to four times that of the AGM-86B. Another benefit is that the infrared heat signature has also been reduced or nearly eliminated, aiding the stealthiness of the AGM-129. This was accomplished with the use of high tech materials and coatings.

Applications

Specifications

General characteristics

Type: twin-spool counter-rotating turbofan
Length: 29.5 in (750 mm)
Diameter: 12 in (300 mm) at widest point
Dry weight: 161 lb (73 kg); 99 lb (45 kg) without accessories

Components

Compressor: twin-spool, counter-rotating
Combustors: annular
Turbine: axial
Fuel type: JP-10 (heavy fuel Boron-Slurry)
Oil system: self-contained; 1.3 US pints (620 ml)

Performance

Maximum thrust: 732 lbf (332 kgf; 3.26 kN)
Overall pressure ratio: 30:1
Bypass ratio: 1:1
Turbine inlet temperature: 2,000 °F (1,090 °C) without turbine blade cooling; 1,750 °F (950 °C) with turbine blade cooling
Specific fuel consumption: ≈ 0.25 lb/(lbf⋅h) (7.1 g/(kN⋅s)) at SLS and ISA; some calculations bring this number to 0.15 lb/(lbf⋅h)
Thrust-to-weight ratio: 4.73

References

Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.

External links

v t e Williams Research / Williams International aircraft engines
Turbofans	EJ22 F107 F112 F121 F122 FJ33 FJ44 J400 WR2 WR19 WR24

v t e United States military gas turbine aircraft engine designation system
Turbojets	J30 J31 J32 J33 J34 J35 J36 J37 XJ38 J39 J40 XJ41 J42 J43 J44 J45 J46 J47 J48 XJ49 J51 J52 J53 J54 J55 J56 J57 J58 J59 J60 J61 J63 J65 J67 J69 J71 J73 J75 J79 J81 J83 J85 J87 J89 J91 YJ93 J95 J97 J99 J100 YJ101 J102 J400 J401 J402 J403 J700
Turboprops/ Turboshafts	T30 T31 T33 T34 T35 T36 T37 T38 T39 T40 T41 T42 T43 T44 T45 T46 T47 T48 T49 T50 T51 T52 T53 T54 T55 T56 (variants) T57 T58 T60 T61 T62 T63 T64 T65 T66 T67 T68 T69 T70 T71 T72 T73 T74 T76 T78 T80 T100 T101 T400 T405 T406 T407 T408 T700 T701 T702 T703 T706 T708 LHTEC T800 APW T800 T900 T901
Turbofans	TF30 TF31 TF32 TF33 TF34 TF35 TF37 TF39 TF41 F100 F101 F102 F103 F104 F105 F106 F107 F108 F109 F110 F112 F113 F117 F118 F119 YF120 F121 F122 F124 F125 F126 F127 F128 F129 F130 F135 F136 F137 F138 F400 F401 F402 F404 F405 F408 F412 F414 F415
Adaptive cycle engines	XA100 XA101 XA102 XA103

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