The General Electric TF39 is a high-bypass turbofan engine that was developed to power the Lockheed C-5 Galaxy. The TF39 was the first high-power, high-bypass jet engine developed. The TF39 was further developed into the CF6 series of engines, and formed the basis of the LM2500 and LM6000 marine and industrial gas turbine. On September 7, 2017, the last active C-5A powered with TF39 engines made its final flight to Davis-Monthan Air Force Base for retirement.[1][2] The TF39 was effectively retired, and all remaining active C-5 Galaxys are now powered by F138 (General Electric CF6-80C2) engines.
TF39
A TF39 on a C-5 Galaxy at ILA (Internationale LuftfahrtAusstellung) in Berlin, 2008
The United States Air Force opened the "CX-X Program" in 1964, intending to produce a next-generation strategic 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 turbofan was a huge leap in engine performance, offering a thrust of 43,000 pounds, while improving fuel efficiency by about 25%.[3] The TF39 had an 8:1 bypass ratio, a 25:1 compressor pressure ratio, and a 2,500 °F (1,370 °C) turbine temperature made possible by advanced forced-air cooling. 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.
Designedit
TF39s on a C-5 Galaxy, from the rearTF-39 on display at the 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 was a revolutionary 1960s engine rated from 41,000 to 43,000 lbf (191 to 205 kN) of thrust. It introduced use of a large by-pass ratio which, together with advances in core technology, contributed to a significant improvement in fuel efficiency over engines available at the time.
The engine included features developed from previous GE engines:
Snubbered first stage fan blades (snubbers, or mid-span shrouds, had been introduced by GE on the YJ93 first stage compressor blades[5])
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.[4] This aircraft had two X353-5 engines, each consisting of a 62.5-inch-diameter[6] lift-fan driven by a gas generator (J85). The bpr in VTOL operation was 12.3.[7] 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.[4] For the CX-X program GE demonstrated a half-scale engine, the GE1/6, with 15,830 lb thrust and an sfc of 0.336.[8] This was developed into the TF39 with a 97 in diameter fan.
A Boeing B-52E (Serial Number 57-0119) testing a TF39 on the right inboard engine pod. The TF39 has more than double the thrust of the twin Pratt & Whitney J57s that were originally in that spot.
^Smith, Hanna (8 September 2017). "And then there were none, the final C-5A departs Westover ARB for retirement > Westover Air Reserve Base > Article Display".
^Balik, Roland (12 April 2016). "An era of Dover-built TF39 engines throttles down". Air Mobility Command. Retrieved 9 February 2023.
^General Electric - CF6 history 2009-01-27 at the Wayback Machine
^ abcde"seven decades of progress" General Electric, ISBN0-8168-8355-6, Aero Publishers Inc. p.152
^"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
^"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
^"Jet Propulsion for Aerospace Applications" Second Edition, Hesse and Mumford, Pitman Publishing Corporation, 1964, Table 11.1
^"The Development of Jet and Turbine Engines", 4th edition, Bill Gunston, ISBN0 7509 4477 3, p. 192
^Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 119
Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN0-7509-4479-X.
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January 01, 1970
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The General Electric TF39 is a high bypass turbofan engine that was developed to power the Lockheed C 5 Galaxy The TF39 was the first high power high bypass jet engine developed The TF39 was further developed into the CF6 series of engines and formed the basis of the LM2500 and LM6000 marine and industrial gas turbine On September 7 2017 the last active C 5A powered with TF39 engines made its final flight to Davis Monthan Air Force Base for retirement 1 2 The TF39 was effectively retired and all remaining active C 5 Galaxys are now powered by F138 General Electric CF6 80C2 engines TF39 A TF39 on a C 5 Galaxy at ILA Internationale LuftfahrtAusstellung in Berlin 2008 Type High bypass turbofan National origin United States Manufacturer GE Aviation First run 1964 Major applications Lockheed C 5 Galaxy Number built 463 Developed into General Electric CF6 General Electric LM2500 Contents 1 Development 2 Design 3 Applications 4 Specifications TF39 1C 4 1 General characteristics 4 2 Components 4 3 Performance 5 See also 6 References 7 External linksDevelopment editThe United States Air Force opened the CX X Program in 1964 intending to produce a next generation strategic 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 turbofan was a huge leap in engine performance offering a thrust of 43 000 pounds while improving fuel efficiency by about 25 3 The TF39 had an 8 1 bypass ratio a 25 1 compressor pressure ratio and a 2 500 F 1 370 C turbine temperature made possible by advanced forced air cooling 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 Design edit nbsp TF39s on a C 5 Galaxy from the rear nbsp TF 39 on display at the 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 was a revolutionary 1960s engine rated from 41 000 to 43 000 lbf 191 to 205 kN of thrust It introduced use of a large by pass ratio which together with advances in core technology contributed to a significant improvement in fuel efficiency over engines available at the time The engine included features developed from previous GE engines Variable stator vanes used in the J79 CJ805 4 Turbine cooling techniques advanced from the J93 used in the XB 70 4 Cascade type thrust reverser from the CJ805 4 Snubbered first stage fan blades snubbers or mid span shrouds had been introduced by GE on the YJ93 first stage compressor blades 5 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 4 This aircraft had two X353 5 engines each consisting of a 62 5 inch diameter 6 lift fan driven by a gas generator J85 The bpr in VTOL operation was 12 3 7 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 4 For the CX X program GE demonstrated a half scale engine the GE1 6 with 15 830 lb thrust and an sfc of 0 336 8 This was developed into the TF39 with a 97 in diameter fan Applications editLockheed C 5A B C GalaxySpecifications TF39 1C edit nbsp A Boeing B 52E Serial Number 57 0119 testing a TF39 on the right inboard engine pod The TF39 has more than double the thrust of the twin Pratt amp Whitney J57s that were originally in that spot Data from 9 General characteristics Type Turbofan Length 312 in 792 cm Diameter 97 in 246 cm Dry weight 8000 lb 3630 kg Components Compressor Axial 2 stage fan 16 stage high pressure compressor Combustors Annular Turbine Axial 2 stage high pressure turbine 6 stage low pressure turbine Performance Maximum thrust 43 300 lbf 193 kN Overall pressure ratio 25 1 Fuel consumption 3 7646 lb s 1 7075 kg s Specific fuel consumption 0 313 lb lbf h 8 9 g kN s Thrust to weight ratio 5 4See also editRelated development General Electric CF6 General Electric LM2500 Comparable engines Pratt amp Whitney JT9D Progress D 18T Rolls Royce RB211 Related lists List of aircraft enginesReferences edit Smith Hanna 8 September 2017 And then there were none the final C 5A departs Westover ARB for retirement gt Westover Air Reserve Base gt Article Display Balik Roland 12 April 2016 An era of Dover built TF39 engines throttles down Air Mobility Command Retrieved 9 February 2023 General Electric CF6 history Archived 2009 01 27 at the Wayback Machine a b c d e seven decades of progress General Electric ISBN 0 8168 8355 6 Aero Publishers Inc p 152 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 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 Jet Propulsion for Aerospace Applications Second Edition Hesse and Mumford Pitman Publishing Corporation 1964 Table 11 1 The Development of Jet and Turbine Engines 4th edition Bill Gunston ISBN 0 7509 4477 3 p 192 Gas Turbine Engines Aviation Week amp Space Technology Source Book 2009 p 119 Gunston Bill 2006 World Encyclopedia of Aero Engines 5th Edition Phoenix Mill Gloucestershire England UK Sutton Publishing Limited ISBN 0 7509 4479 X External links edit nbsp Wikimedia Commons has media related to General Electric TF39 General Electric TF39 website Retrieved from https en wikipedia org w index php title General Electric TF39 amp oldid 1190298414, wikipedia, wiki, book, books, library,
