Williams F112: Difference between revisions

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<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. -->
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{|{{Infobox Aircraft Begin
{|{{Infobox aircraft begin
|name= F112
|name= F112
|image= File:Williams International F112 NMUSAF.jpg
|image= Williams Research F112-WR-100.jpg
|caption= An F112 engine on display at the National Museum of the USAF, with an X-36
|caption= An F112 engine on display at the [[National Museum of the United States Air Force]]
}}
}}
{{Infobox Aircraft Engine
{{Infobox Aircraft Engine
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|program cost =
|program cost =
|unit cost =
|unit cost =
|developed from =
|developed from = [[Williams F107]]
|developed into = [[Williams F107]]
|developed into =
|variants with their own articles =
|variants with their own articles =
}}
}}
|}
|}


The '''Williams F112''' is a small [[turbofan]] engine made by [[Williams International]] designed to power [[cruise missile]]s. Although Williams originally designed these small turbofans to power target drones, 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. It has been used as the powerplant for the [[AGM-129 ACM|AGM-129 Advanced Cruise Missile]]and the AGM-86B advanced cruise missile, as well as the experimental [[McDonnell Douglas X-36|X-36]] and [[Boeing X-50|X-50]].
The '''Williams F112''' is a small [[turbofan]] engine made by [[Williams International]] designed to power [[cruise missile]]s. It has been used as the powerplant for the [[AGM-129 ACM|AGM-129 Advanced Cruise Missile]] and the [[AGM-86 ALCM|AGM-86B]] advanced cruise missile, as well as the experimental [[McDonnell Douglas X-36|X-36]] and [[Boeing X-50|X-50]].


==Design and development==
⚫
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 four times that of the AGM-86B. Another benefit is 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.

Although Williams originally designed these small turbofans to power target drones while aiming for a contract in the [[AGM-86_ALCM#SCAD|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 ACM|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-86 ALCM#AGM-86B|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==
==Applications==
*[[AGM-129 ACM]]
* [[AGM-129 ACM]]
*[[AGM-86B]]
* [[Boeing X-50]]
*[[Boeing X-50]]
* [[McDonnell Douglas X-36]]
*[[McDonnell Douglas X-36]]


==Specifications==
==Specifications==
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|ref=
|ref=
|type=Twin-spool counter rotating turbofan
|type=Twin-spool counter rotating turbofan
|length= 29.5 in.
|length= 29.5 in
|diameter= 12 in. (at widest point)
|diameter= 12 in (at widest point)
|weight=161 lb (99 lbs without accessories)
|weight=161 lb (99 lb without accessories)
|compressor= centrifugal
|compressor= Two-spool, counter-rotating
|combustion= annular
|combustion= annular
|turbine= axial
|turbine= axial
|fueltype= heavy fuel Boron-Slurry (aka JP-10)
|fueltype= heavy fuel Boron-Slurry (aka [[JP-10 (fuel)|JP-10]])
|oilsystem= self contained 1.3 pints (0.61 liters)
|oilsystem= self contained 1.3 pints (0.61 liters)
|power=
|power=
|thrust=1000 lb
|thrust=732Ib (332kg)
|compression=30:1
|compression=30:1
|bypass=1:1
|bypass=1:1
|TIT=
|TIT=
|turbinetemp= TIT 2000 degs F (1093 degs C) with turbine blade cooling; 1750 degs F (954 degs C) without turbine blade cooling
|turbinetemp= TIT 2000 deg F (1093 deg C) without turbine blade cooling; 1750 deg F (954 deg C) with turbine blade cooling
|fuelcon=
|fuelcon=
|specfuelcon= apprx 0.25lbs/lb/hr (but some calculations bring this number to 0.15 lbs/lb/hr)
|specfuelcon= approx 0.25 lb/(lbf h) (but some calculations bring this number to 0.15 lb/(lbf h)
|power/weight=
|power/weight=
|thrust/weight=10 to 1
|thrust/weight=4.73
}}
}}


==See also==
==See also==
{{Aircontent
{{Aircontent
|related=
|related=
*[[Williams F107]]
* [[Williams F107]]

|similar engines=
|similar engines=

|lists=
|lists=
*[[List of aircraft engines]]
* [[List of aircraft engines]]

|see also=
|see also=
}}
}}
Line 71: Line 71:
==References==
==References==
{{reflist}}
{{reflist}}
* {{cite book |last= Leyes II|first=Richard A. |author2=William A. Fleming |title= The History of North American Small Gas Turbine Aircraft Engines |publisher= Smithsonian Institution |location= Washington, DC| date= 1999 |isbn=1-56347-332-1 }}
http://www.forecastinternational.com/samples/F655_CompleteSample.pdf


==External links==
==External links==
{{Commons category}}
*[http://www.nationalmuseum.af.mil/factsheets/factsheet.asp?id=886 National Museum of the USAF F112 fact sheet]
* [http://www.nationalmuseum.af.mil/Visit/MuseumExhibits/FactSheets/Display/tabid/509/Article/195684/williams-international-f112-wr-100-turbofan.aspx National Museum of the USAF F112 fact sheet]
* [https://web.archive.org/web/20100705045227/http://www.forecastinternational.com/samples/F655_CompleteSample.pdf Archived "Aviation Gas Turbine Forecast" sample, 2009 by Forecast International]
* [http://www.leteckemotory.cz/motory/williams/williams.php F112 on LeteckeMotory.cz] (cs)


{{Williams aeroengines}}
{{Williams aeroengines}}
{{USAF gas turbine engines}}
{{USAF gas turbine engines}}
{{Aviation lists}}
{{aeroengine-specs}}
{{aeroengine-specs}}


[[Category:Low-bypass turbofan engines]]
[[Category:Low-bypass turbofan engines]]
[[Category:Turbofan engines 1970-1979]]
[[Category:1970s turbofan engines]]
[[Category:Williams aircraft engines|F112]]
[[Category:Centrifugal-flow turbojet engines]]

Latest revision as of 07:45, 10 January 2024

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[edit]

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[edit]

Specifications[edit]

General characteristics

  • Type: Twin-spool counter rotating turbofan
  • Length: 29.5 in
  • Diameter: 12 in (at widest point)
  • Dry weight: 161 lb (99 lb without accessories)

Components

  • Compressor: Two-spool, counter-rotating
  • Combustors: annular
  • Turbine: axial
  • Fuel type: heavy fuel Boron-Slurry (aka JP-10)
  • Oil system: self contained 1.3 pints (0.61 liters)

Performance

See also[edit]

Related development

Related lists

References[edit]

  • 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[edit]

Wikimedia Commons has media related to Williams F112.
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