View source for General Electric TF39

{{short description|Turbofan aircraft engine}}
{{infobox aero engine
 |name= TF39
 |image= File:ILA 2008 PD 083.JPG
 |caption= A TF39 on a C-5 Galaxy at ILA (''Internationale LuftfahrtAusstellung'') in Berlin, 2008
 |engine_type= High-bypass [[turbofan]]
 |national_origin= United States
 |manufacturer= [[GE Aviation]]
 |first_run= 1964
 |major_applications= [[Lockheed C-5 Galaxy]]
 |number_built= 463
 |developed_from=
 |variants_with_their_own_articles=
 |developed_into= {{ubl | [[General Electric CF6]] | [[General Electric LM2500]] }}
}}

The '''General Electric TF39''' was a [[high-bypass turbofan engine]] that was developed to power the [[Lockheed C-5 Galaxy]]. It was the first high-bypass jet engine developed, which became the foundation for the [[General Electric CF6]] Jet Engine and the [[General Electric LM2500]] Marine Turbine

==Development==
The [[United States Air Force]] opened the "CX-X Program" in 1964, intending to produce a next-generation strategic [[cargo aircraft|airlifter]]. Of the several airframe and engine proposals returned for consideration, Lockheed's aircraft and General Electric's engine were selected for the new design in 1965.

The high-bypass ratio of 8:1 for the TF-39 had its origins in the lift-fan technology demonstrated by GE in the [[XV-5 Vertifan]] aircraft.<ref name=ge /> This aircraft had two X353-5 engines, each consisting of a 62.5-inch-diameter<ref>"Aerodynamic characteristics of a Large-Scale Model with a High Disk Loading Lift Fan Mounted in the Fuselage" Aoyagi, Hickey and deSavigny, NASA TN D-775</ref> lift-fan driven by a gas generator (J85). The bpr in VTOL operation was 12.3.<ref>"Jet Propulsion for Aerospace Applications" Second Edition, Hesse and Mumford, Pitman Publishing Corporation, 1964, Table 11.1</ref> This tip-turbine driven lift-fan concept was turned 90 degrees and developed as an 80-inch-diameter "cruise fan" demonstrator, driven by a J79 gas generator.<ref name=ge /> For the CX-X program GE demonstrated a half-scale engine, the GE1/6, with 15,830&nbsp;lb thrust and an sfc of 0.336.<ref>"The Development of Jet and Turbine Engines", 4th edition, Bill Gunston, {{ISBN|0 7509 4477 3}}, p. 192</ref> This was developed into the TF39 with a 97 in diameter fan.

The high-bypass substantially improved the thrust and fuel consumption compared to the previous GE jetliner turbofan, the CJ805-21.<ref name=ge>"seven decades of progress" General Electric, {{ISBN|0-8168-8355-6}}, Aero Publishers Inc. p.152</ref> It had two and a half times the thrust, while improving [[fuel efficiency]] by about 25%.<ref>[http://geae.com/engines/commercial/cf6/history.html General Electric - CF6 history] {{webarchive|url=https://web.archive.org/web/20090127013821/http://www.geae.com/engines/commercial/cf6/history.html |date=2009-01-27 }}</ref> The first engine went for testing in 1965. Between 1968 and 1971, 463 TF39-1 and -1A engines were produced and delivered to power the C-5A fleet.

The TF39 core was used for the [[General Electric CF6|CF6]] series of engines, and the [[General Electric LM2500|LM2500]] and [[LM6000]] marine and industrial gas turbines.

==Design==
[[File:ILA 2008 PD 073.JPG|thumb|TF39s on a C-5 Galaxy, from the rear]]
[[File:23-04-057-TF39.jpg|thumb|TF-39 on display at the [[Museum of Aviation (Warner Robins)|Museum of Aviation]] View looking into the fan showing snubbered blades on the inner half-stage and inlet guide vanes in the outer duct in front of the full stage.]]

The TF39 produced 41,000 to 43,000 [[Pound-force|lb]] (191 to 205 [[kilonewton|kN]]) of thrust. 
It had an 8:1 bypass ratio, a 25:1 compressor pressure ratio, and a 2,500&nbsp;°F (1,370&nbsp;°C) turbine temperature made possible by the latest cooling technology.

The engine included features developed from previous GE engines:
* Variable stator vanes (used in the J79/CJ805<ref name=ge />)
* Turbine cooling techniques (more advanced than used on the YJ93<ref name=ge />)
* Cascade-type [[thrust reverser]] (from the CJ805<ref name=ge />)
* Snubbered first stage fan blades (snubbers, or mid-span shrouds, had been introduced by GE on the YJ93 first stage compressor blades<ref name=koff>"Gas Turbine Technology Evolution: A Designer's Perspective" Bernard L. Koff, Journal of Propulsion and Power, Vol.20 No. 4, July–August 2004, p.591</ref>)

By modern standards the Low Pressure Compressor on the TF-39 is fairly unique as a single T-stage is mounted upstream of the fan rotor, rather than behind it. Although this T-stage supercharges the inner section of the fan rotor, not all of this airstream enters the High Pressure Compressor as a fair proportion also enters the bypass duct to supplement the air discharging from the outer section of the fan. In other words there are three streams leaving the fan, two of which enter the bypass duct.<ref>https://aviation.stackexchange.com/questions/51747/why-does-the-cf6-have-a-lower-bypass-ratio-than-the-tf39</ref>

==Operational history==
On September 7, 2017, the last C-5A powered with TF39 engines made its final flight to Davis-Monthan Air Force Base for retirement.<ref>{{cite web |url=https://www.westover.afrc.af.mil/News/Article-Display/Article/1303782/and-then-there-were-none-the-final-c-5a-departs-westover-arb-for-retirement/ |title = And then there were none, the final C-5A departs Westover ARB for retirement > Westover Air Reserve Base > Article Display |date=8 September 2017|last=Smith |first=Hanna}}</ref><ref>{{cite web |last1=Balik |first1=Roland |title=An era of Dover-built TF39 engines throttles down |url=https://www.amc.af.mil/News/Article-Display/Article/785826/an-era-of-dover-built-tf39-engines-throttles-down/ |website=Air Mobility Command |access-date=9 February 2023 |date=12 April 2016}}</ref> The only application for the TF39, the Galaxy military transport, was re-engined with the more modern F138-GE-102, a military version of the [[General Electric CF6-80C2]]. Re-engining for the whole fleet took place from 2008 to 2018.

==Applications==
* [[Lockheed C-5 Galaxy|Lockheed C-5A/B/C Galaxy]]

==Specifications (TF39-1C)==
[[File:Boeing JB-52E (SN 57-0119) in flight 061127-F-1234S-026.jpg|thumb|A Boeing B-52E (Serial Number 57-0119) testing a TF39 on the right inboard engine pylon. The TF39 has more than double the thrust of the two [[Pratt & Whitney J57]]s that were normally on all four pylons.]]
{{jetspecs
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|ref=<ref>Gas Turbine Engines. ''Aviation Week & Space Technology Source Book 2009''. p. 119</ref>
|type= [[Turbofan]]
|length=312 in (792 cm)
|diameter=97 in (246 cm)
|weight=8000 lb (3630 kg)
|compressor=Axial, low pressure compressor, comprising single stage booster and a single stage fan, 16-stage high-pressure compressor
|combustion=[[Combustor#Annular|Annular]]
|turbine=Axial, 2-stage high-pressure turbine, 6-stage low-pressure turbine
|fueltype=
|oilsystem=
|power=
|thrust=43,300 lbf (193 kN)
|compression=25:1
|aircon=
|turbinetemp=
|fuelcon=~3.7646 lb/s (1.7075 kg/s)
|specfuelcon={{cvt|0.313|tsfc}}
|power/weight=
|thrust/weight=5.4
}}

==See also==
{{Aircontent
|related=
* [[General Electric CF6]]
* [[General Electric LM2500]]
|similar engines=
* [[Pratt & Whitney JT9D]]
* [[Progress D-18T]]
* [[Rolls-Royce RB211]]
|lists=
* [[List of aircraft engines]]
|see also=
}}

==References==
{{reflist}}
* {{cite book |last= Gunston |first= Bill |title= World Encyclopedia of Aero Engines, 5th Edition |year= 2006 |publisher= Sutton Publishing Limited |location= Phoenix Mill, Gloucestershire, England, UK |isbn= 0-7509-4479-X }}

==External links==
{{Commons category}}
* [https://web.archive.org/web/20070428082857/http://www.geae.com/engines/military/tf39/index.html General Electric TF39 website]

{{General Electric aeroengines}}
{{USAF gas turbine engines}}
{{USAF system codes}}

[[Category:High-bypass turbofan engines]]
[[Category:General Electric aircraft engines|TF39]]
[[Category:1960s turbofan engines]]