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Aviation History
1969
1969 - 0033.PDF
FLIGHT International, 2 January 1969 21 GENERAL ELECTRIC (Aircraft Engine Group, General Electric Company), West Lynn, Massachusetts, USA General Electric Military Engine Division TF39 Military twin-spool turbofan. Under development and in production to power Lockheed C-5A Galaxy, the TF39 is financed under $459 million USAF programme covering supply of 258 engines for 58 C-5As. More than 10,000hr testing has been completed by 28 development engines including over 300hr flying by XTF39s and YTF39s in the Boeing NB-52E FTB and three prototype C-5As. An initial 150hr type-test has been completed and deliveries have been made of production-standard engines. Over-expenditure on contract price now subject of discussions with Department of Defence. (TF39-GE-1) One and one-half stage fan, 16-stage h-p compressor, annular combustor, two-stage h-p turbine, five-stage 1-p turbine. Take-off 41,0001b; b.p.r. 8:1; mass flow l,5491b/sec; pressure ratio (overall) 25:1; length 324in; diameter lOOin; weight 7,0261b. TF34 Military twin-spool turbofan. Winning entry in the USN's engine competition for the VSX anti-submarine warfare project. Two TF34-GE-2s rated in the 9,0001b thrust category will power the VSX aircraft, .first flight of which is planned for June 1971. GE was awarded a four-year Navy development contract for the TF34 in April 1968: first run of the engine is scheduled for this summer. In configuration the TF34 is a high b.p.r. turbofan with a variable stator compressor, annular combustor, and air-cooled turbine. Extensive use is made of TF39 technology. GE12 Military free-turbine turboshaft. A new 1,500 s.h.p. direct- drive free-turbine turboshaft for future military VTOL aircraft being developed in competition with the Pratt & Whitney ST9. Demonstrator GE12s are being built and tested for lOOhr under a two-year programme initiated in August 1967 under US Army contract. Designed to provide improved performance capabilities coupled with rugged simplicity for field maintenance. GE9 Military turbofan. A new engine design by GE to meet propulsion needs of USAF's AMSA project and General Dynamics B-111G4 strategic bomber project. FX Demonstrator Military twin-spool augmented turbofan. Under $11 million USAF contracts awarded to both GE and Pratt & Whitney in August 1968 (following requests for proposals issued in April), the two companies are building and will test afterburning turbofan demonstrator engines for USAF's FX advanced air- superiority fighter project. Eventual value of each contract is likely to be $50 million. Same engine is also expected to meet propulsion needs of US Navy's VFX-2 advanced fighter project. The turbofans, to be based on current US lift-cruise engine technology, are of advanced lightweight design and are rated around 26,0001b. Decision between competing engines to be made late this year and FX is scheduled to fly mid-1972. Winning engine likely to be supplied under direct sub-contract from FX prime contractor. GE1 Civil and military single-shaft turbojet. Provides standard gas generator core engine, either direct or scaled-up for all new GE developments except GE4. Ensures continuity of experience and economies in development costs. Basic core engine rated at 5,0001b; length approximately 70in; diameter 24in. Seven basic variants have been projected and/or tested by Gfi. (GE1 augmented turbofan) GE1 core engine energising low b.p.r. front fan, and equipped with afterburner. Thrust bracket 15,0001b to 25,0001b. (GE1 turboshaft) GE1 core engine energising free-turbine with direct-drive front shaft. Power category, 10,000 s.h.p. (GE1 augmented vectored turbofan) GE1 core engine energising low b.p.r. front fan with full fan/exhaust flow exiting via single rear vectoring nozzle. Thrust bracket 10,0001b to 20,0001b. (GE1 augmented turbojet) GE1 core engine equipped with after burner. Thrust category 7,5001b. (GE1 cruise fan) GE1 core engine energising remote tip-turbine- driven cruise fan of high b.p.r. Thrust category, 26,0001b. (GE1 lift fan) GE1 core engine energising remote tip-turbine- driven lift fan of high b.p.r. Thrust category, 27,5001b. (GET turbofan) GE1 core engine energising high b.p.r. front fan. Thrust category, 20,0001b. Applications Sundry applications for the GE1 family have been proposed. Typical are the Messerschmitt MeP.2020 project, 2XGE1 cruise fans (14,0001b), and Northrop Project 530, 2XGE1 augmented turbojets. GE1/1© Military twin-spool augmented vectored turbofan. Com prises GE1 core engine with moderate b.p.r, front fan, afterburner and (optional) thrust vectoring nozzle. Demonstrator GEl/lOs have exceeded all USAF contract performance commitments and the twin-knuckle swivelling nozzle has been tested behind Rolls-Royce RB153 augmented turbofan by MAN Turbo under contract to GE, GE1/10 has been proposed by GE for USAF's FX and USN's VFX projects. GE1/J1A1 Military singe-shaft turbojet. Utilising GE1 gas generator with the addition of an afterburner, provides turbojet for new advanced performance supersonic fighters and intercepters, of 7,5001b thrust. Length and diameter: approximately 140in and 24in. J85 Military single-shaft turbojet. Extensively installed in light fighter and trainer aircraft. Manufacture licensed to Orenda and Alfa Romeo. Has also been used as gas generator/turbo jet for GE lift-fan installations. More than 6,000 J85s built. Applications Canadair CF-5A and CF-5D, 2XJ85-GE-15 (4,3001b with afterburning). Canadair CL-41A, 1 XJ85-CAN-40 (2,6331b); Canadair CL-41G, 1 XJ85/J4 (2,9501b). CASA SF-5B, 2XJ85-GE-13 (4,0801b). Cessna A-37B, 2XJ85-GE-17A (2,4001b). Convair F-106, 2XJ85 (in propulsion research pods). Fairchild Hiller AC-119K Gunship Three, 2XJ85-GE-17 (2,8501b) booster units. Fairchild Hiller FH-V4 project, 4XJ85/J1. Fairchild C-123K, 2XJ85-GE-17 (2,8501b) booster units. Fiat G-91Y, 2XJ85-GE-13 (2,7201b basic. 4,0801b with afterburning). Lockheed XV-4B, 6XJ85-GE-19 (3,0151b). McDonnell ADM-20C Quail, IX J85-GE-7 (2,4501b). North American Rockwell OV-10A Bronco, 1XJ85 booster unit. Northrop T-38A Talon, 2XJ85-GE-5A (2,6801b basic, 3,8501b with afterburning). Northrop F-5A and F-5B, 2XJ85-GE-13 (2,7201b basic, 4,0801b with afterburning). Saab 105XT, 2XJ85-GE-17B (2,8501b). (J85-GE-13) Eight-stage compressor, annular combustor, two-stage turbine. Close-coupled afterburner with variable nozzle. Take-off 2,7201b basic and 4,0801b with afterburning; mass flow 441b/sec; pressure ratio 7:1; length 108.9in; diameter 22.0in; weight 5971b. J79 Military single-shaft turbojet. Major US Mach 2 turbojet with extensive application in Lockheed F-104 and McDonnell F-4. Manufacture licensed to MAN-Turbo, Ishikawajima-Harima Heavy Industries, Fabrique Nationale, Fiat and Orenda. More than 10,000 J79s now built. Applications Canadair CF-104 and CF-104D, 1XJ79-OEL-7 (10,0001b basic, 15,8001b with afterburning). Convair B-58A Hustler, 4XJ79-GE-5C (10,000ib basic, 15,6001b with afterburning). Lock heed F-104A and F-104B, 1XJ79-GE-3A (9,6001b basic, 14,8001b with afterburning). Lockheed F-104C, D & F, 1XJ79-GE-7A (10,Q001b basic, 15,8001b with afterburning); Lockheed/Mitsubishi F-104J & DJ, 1XJ79-GE/IHI-11A (10,0001b basic, 15,8001b with afterburning); Lockheed/European Consortium F-104G, 1XJ79-GE/ MAN/Fiat/FN-llA (10,0001b basic, 15,8001b with afterburning); Lockheed TF-104G, 1XJ79-GE-11A (10,0001b basic, 15,8001b with afterburning); Lockheed F-104S, 1XJ79-GE-19 (11,8701b basic, 17,9001b with afterburning). McDonnell Phantom F-4B, RF-4B and F-4G, 2XJ79-GE-8A (10,9001b basic, 17,0001b with afterburning); McDonnell Phantom F-4C, RF-4C and F-4D, 2XJ79-GE-15 (10,9001b basic, 17,0001b with afterburning); McDonnell Phantom F-4E, 2XJ79-GE-17 (11,8701b basic, 17,9001b with afterburning); McDonnell Phantom F-4J, 2XJ79-GE-10 (11,8701b basic, 17,9001b with afterburning). North American RA-5C Vigilante, 2XJ79-GE-8 (10,9001b basic, 17,0001b with afterburning). (J79-GE-15) Seventeen-stage compressor, cannular combustor, with ten flame tubes, three-stage turbine. Close-coupled afterburner. Variable convergent-divergent nozzle. Take-off 10,9001b basic and 17,0001b with afterburning; mass flow 169lb/sec; pressure Iratio 12.9:1; length 208.45in; diameter 38.3in; weight 3,6851b. | J93 Military single-shaft augmented turbojet. Sole application is the North American B-70A Valkyrie supersonic research vehicle. Has provided valuable high Mach number experience for application During 1968 the General Electric GEI/10 military twin-spool augmented turbofan of around 7,0001b basic thrust exceeded all its design performance requirements as laid down by the USAF
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