Williams FJ44: Difference between revisions - Wikipedia


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{{short description|Small turbofan engine}}

{{primary|date=November 2021}}

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The '''Williams FJ44''' is a family of small, two-spool, [[turbofan]] engines produced by [[Williams International]]/[[Rolls-Royce Holdings|Rolls-Royce]] for the [[light business jet]] market. Until the recent boom in the [[very light jet]] market, the FJ44 was one of the smallest turbofans available for civilian applications. Although basically a Williams design, Rolls-Royce was brought into the project at an early stage to design, develop, and manufacture an air-cooled high-pressure (HP) turbine for the engine. The FJ44 first flew on July 12, 1988 on the [[Scaled Composites Triumph|Scaled Composites/Beechcraft Triumph]] aircraft.

The [[Williams FJ33]] is a newer, smaller engine based on the basic FJ44 design.

==Development==

==Design and development==

Production started in 1992 with the {{Convert|1900|lbf|kN|abbr=on|lk=on}} thrust '''FJ44-1A'''. The '''FJ44-1C''' is derated to {{Convert|1500|lbf|kN|abbr=on}}.

Production started in 1992 with the {{Convert|1900|lbf|kN|abbr=on|lk=on}} thrust '''FJ44-1A''', which comprises a {{Convert|20.9|in|mm|abbr=on}} diameter single stage [[blisk]] fan plus a single intermediate pressure (IP) booster stage, driven by a 2 stage low pressure (LP) turbine, supercharging a single stage centrifugal high pressure (HP) compressor, driven by a single stage uncooled high pressure (HP) turbine. The combustor is an impingement cooled annular design. Fuel is delivered to the combustor through an unusual rotating fuel nozzle system, rather than the standard fuel-air mixers or vapourisers. The bypass duct runs the full length the engine. Specific fuel consumption at 1900&nbsp;lbf (8.45&nbsp;kN) thrust at SLS, ISA is understood to be 0.456&nbsp;lb/(hr lbf). A derated version, the {{Convert|1500|lbf|kN|abbr=on}} thrust '''FJ44-1C''' has an [[Specific fuel consumption (thrust)|SFC]] of {{Convert|0.460|lb/lbf/h|kg/kN/h|abbr=on}}.<ref>[http://www.williams-int.com/high/product/engines/fj44-1.htm FJ44-1] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref><ref>[http://defence.rolls-royce.com/FJ44-gas-turbines-for-trainer-aircraft/ FJ44 for military trainer aircraft] at [http://defence.rolls-royce.com defence.rolls-royce.com], Accessed 2006-05-07</ref>

The uprated to {{Convert|2300|lbf|kN|abbr=on}} '''FJ44-2A''' was introduced in 1997.

The {{Convert|2820|lbf|kN|abbr=on}} thrust '''FJ44-3A''' was introduced in 2004.

In 2005, a new low end version, the '''FJ44-1AP''', was introduced, with a {{Convert|1965|lbf|kN|abbr=on}} takeoff thrust.

Released in 2007 was the new {{Convert|3600|lbf|kN|abbr=on}} thrust '''FJ44-4''', which has a hi-tech fan of larger diameter than the -3 unit.<ref>[http://www.williams-int.com/information.html?pid=1 FJ44-4] at [http://www.williams-int.com www.williams-int.com], AccessedIn 2010-03-12</ref> As of March 2010, this engine was only in use on the [[Cessna CitationJet#Model 525C|Cessna CJ4]], and since 2018 also on the new [[Pilatus PC-24]].▼

==Design==

An uprated version, the {{Convert|2300|lbf|kN|abbr=on}} thrust '''FJ44-2A''', was introduced in 1997. It has a larger {{Convert|21.7|in|mm|abbr=on}} diameter fan, with two additional booster stages to increase core flow. Owing to stressing considerations, the centrifugal compressor is throttled-back aerodynamically to a lower HPC pressure ratio than the -1. Other features include an exhaust mixer and an electronic fuel control unit.<ref>[http://www.williamsint.com/high/product/engines/fj44-2.htm FJ44-2] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref> The {{Convert|2400|lbf|kN|abbr=on}} thrust '''FJ44-2C''' is similar to the -2A, but incorporates an integrated hydromechanical fuel control unit.▼

The FJ44-1A has a single stage [[blisk]] fan plus a single intermediate pressure (IP) booster stage, both driven by a 2 stage low pressure (LP) turbine, and supercharging a single stage centrifugal high pressure (HP) compressor, driven by a single stage uncooled high pressure (HP) turbine. The combustor is an impingement cooled annular design. Fuel is delivered to the combustor through an unusual rotating fuel nozzle system, rather than the standard fuel-air mixers or vapourisers. The bypass duct runs the full length of the engine.

Further updates include the 2004 introduction of the {{Convert|2820|lbf|kN|abbr=on}} thrust '''FJ44-3A''', which is similar to the -2A, but features an increased diameter fan and dual channel [[FADEC]] (Full Authority Digital Engine Control) unit.<ref>[http://www.williams-int.com/high/product/engines/fj44-3.htm FJ44-3] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref> The {{Convert|2490|lbf|kN|abbr=on}} thrust '''FJ44-3A-24''' is a derated version of the -3A.▼

The FJ44-2A has two additional booster compressor stages.

In 2005, a new low end version, the '''FJ44-1AP''', was introduced, with a {{Convert|1965|lbf|kN|abbr=on}} takeoff thrust, 5% better specific fuel consumption, and lower internal temperatures. The -1AP is similar to the -1A, except for a higher pressure ratio fan, a new combustor and LP turbine, a new full length bypass duct/exhaust mixer and a dual channel FADEC.<ref>[http://www.williams-int.com/high/product/engines/fj44-1ap.htm FJ44-1AP] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref>▼

▲Released in 2007 was the new {{Convert|3600|lbf|kN|abbr=on}} thrust '''FJ44-4''', which has a hi-tech fan of larger diameter than the -3 unit.<ref>[http://www.williams-int.com/information.html?pid=1 FJ44-4] at [http://www.williams-int.com www.williams-int.com], Accessed 2010-03-12</ref> As of March 2010, this engine was only in use on the [[Cessna CitationJet#Model 525C|Cessna CJ4]], and since 2018 also on the new [[Pilatus PC-24]].

==Variants==

;FJ44-1A

: {{Convert|1900|lbf|kN|abbr=on|lk=on}} thrust, production started in 1992, {{Convert|20.9|in|mm|abbr=on}} diameter fan, [[Specific fuel consumption (thrust)|SFC]] at full thrust at SLS, ISA is understood to be 0.456&nbsp;lb/(hr lbf),

;FJ44-1AP

▲In 2005, a new low end version, the '''FJ44-1AP''', was introduced, with a: {{Convert|1965|lbf|kN|abbr=on}} takeoff thrust, introduced in 2005, 5% better specific fuel consumption, and lower internal temperatures. The -1AP is, similar to the -1A, except forwith a higher pressure ratio fan, a new combustor and LP turbine, a new full length bypass duct/exhaust mixer and a dual channel [[FADEC]].<ref>[http://www.williams-int.com/high/product/engines/fj44-1ap.htm FJ44-1AP] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref>

;FJ44-1C

: {{Convert|1500|lbf|kN|abbr=on}} thrust, derated version of the FJ44-1A, SFC of {{Convert|0.460|lb/lbf/h|kg/kN/h|abbr=on}}.<ref>[http://www.williams-int.com/high/product/engines/fj44-1.htm FJ44-1] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref><ref>[http://defence.rolls-royce.com/FJ44-gas-turbines-for-trainer-aircraft/ FJ44 for military trainer aircraft] at [http://defence.rolls-royce.com defence.rolls-royce.com], Accessed 2006-05-07</ref>

;FJ44-2A

▲An uprated version, the: {{Convert|2300|lbf|kN|abbr=on}} thrust '''FJ44-2A''', was introduced in 1997. It has a, larger {{Convert|21.7|in|mm|abbr=on}} diameter fan, with two additional booster stages to increase core flow. Owing to stressing considerations, the centrifugal compressor is throttled-back aerodynamically to a lower HPC pressure ratio than the -1. Other features include an, [[exhaust mixer]] and an electronica fuel [[electronic control unit]].<ref>[http://www.williamsint.com/high/product/engines/fj44-2.htm FJ44-2] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref> The {{Convert|2400|lbf|kN|abbr=on}} thrust '''FJ44-2C''' is similar to the -2A, but incorporates an integrated hydromechanical fuel control unit.

;FJ44-2C

: {{Convert|2400|lbf|kN|abbr=on}} thrust, similar to the -2A with an integrated hydromechanical fuel control unit.

;FJ44-3A

▲Further updates include the 2004 introduction of the: {{Convert|2820|lbf|kN|abbr=on}} thrust '''FJ44-3A''', which2004 isintroduction, similar to the -2A, butwith featuresa an increased diameterlarger fan and dual channel [[FADEC]] (Full Authority Digital Engine Control)|FADEC]] unit.<ref>[http://www.williams-int.com/high/product/engines/fj44-3.htm FJ44-3] at [http://www.williams-int.com www.williams-int.com], Accessed 2006-05-07</ref> The {{Convert|2490|lbf|kN|abbr=on}} thrust '''FJ44-3A-24''' is a derated version of the -3A.

; FJ44-3A-24

: {{Convert|2490|lbf|kN|abbr=on}} thrust, derated -3A.

;FJ44-3AP

: {{Convert|3000|lbf|kN|abbr=on}} thrust.<ref>[http://www.williams-int.com/uploads/Williams%20Fanjet%20Family.pdf Williams Fanjet Family], Accessed 2020-02-20</ref>

;FJ44-4A

: {{Convert|3600|lbf|kN|abbr=on}} thrust, released in 2007, hi-tech fan of larger diameter than the -3 unit.<ref>[http://www.williams-int.com/information.html?pid=1 FJ44-4] at [http://www.williams-int.com www.williams-int.com], Accessed 2010-03-12</ref> Used on the [[Cessna CitationJet#Model 525C|Cessna CJ4]] and the [[Pilatus PC-24]].

;FJ44-4M

;Williams-Rolls F129

:Military designation for the derated FJ44-1C with 1500lbf{{Convert|1500|lbf|kN|abbr=on}} (6.672kN) power outputthrust.

==Applications==

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| [[Pilatus PC-24]] || Business Jet || 2018-

|-

| rowspan=101 | notFJ44-4M delivered{{clarify|date=August 2019}}

| [[Aero L-39NG]] || Jet Trainer<br>Light attack aircraft || under development2022-

|-

| rowspan=9 | not delivered{{clarify|date=August 2019}}

| [[Alenia Aermacchi M-345]] || Jet Trainer || Under development

|-

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| [[Scaled Composites Triumph]] || Business Jet || 1 prototype

|}

{{notelist}}▼

==SpecificationSpecifications==

{| class="wikitable" style="text-align:center"

|+ Type Certificate Data Sheet<ref>{{cite web |url= https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/60398924b8e6df678625831d0047e4be/$FILE/E3GL_Rev_22.pdf |title= Type Certificate Data Sheet NO. E3GL |date= October 4, 2018 |publisher= FAA}}</ref>

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==References==

{{reflist}}

==Notes==

▲{{notelist}}

==External links==