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Aviation History
1969
1969 - 0034.PDF
22 AERO ENGINES 1969 . . . to the GE4 SST engine. Maintenance for Valkyrie engines funded by NASA through to June this year. (J93-GE-3) Eleven-stage compressor, annular combustor, two-stage turbine. Close-coupled afterburner with multi-flap, independently variable, primary and secondary nozzles, Take-off 24,0001b basic, 32,0001b with afterburning: length 237in; diameter 52.5in; weight 5,0001b. TF37 Military free-turbine aft-fan ttirbofan. Military vertically- operating version of civil CF700 turbofan. Applications Bell Lunar Landing Research and Training Vehicles, 1 XTF37-GE-1 (4,2001b). (TF37-GE-1) Configuration and dimensions similar to CF700. Take-off 4,2001b; weight 6751b. T64 Military free-turbine turboshaft. Developed in both turboshaft and turboprop form with varying configuration of reduction gear. Latest version is T64-GE-16 of 3,435 s.h.p. Manufacture licensed to Ishikawajima-Harima Heavy Industries, Rolls-Royce and MAN Turbo. Applications Bell Model 266. 2XT64-GE-16 (3,435 s.h.p.). Boeing Vertol Model 297, 3XT64-GE-16 (3,435 s.h.p.). Lockheed AH-56A. 1 XT64-GE-I6 (3,435 s.h.p.). Lockheed Model CL-879. 4XT64-GE-16 (3,435 s.h.p.). Lockheed Model CL-1026, 2XT64-GE-16 (3,435 s.h.p.). LTV Hiller Ryan XC-142A, 4XT64-GE-1 (2,850 s.h.p.). Sikorsky CH-53A, 2XT64-GE-6 (2,850 s.h.p.) or 2XT64-GE-I2 (3,435 s.h.p.). Sikorsky HH-53A and B, 2XT64-GE-3 (3,080 s.h.p.). Sikorsky CH-54A, 3XT64-GE-16 (3,435 s.h.p.). VFW VC-400. 4XT64-GE-16 (3,435 s.h.p.). Westland WE-02. 4XT64-GE-16 (3,435 s.h.p.). (T64-GE-16) Ten-stage compressor, annular combustor. two-stage compressor-turbine, single-stage power-turbine. Direct drive. Maxi mum power 3,435 s.h.p.; mass flow 26.71b/sec: pressure ratio 13.0:1: length 83.3in: width 25.5in: height 31.3in: weight 6901b. T64 Military free-turbine turboprop. Propeller driving version of T64 turboshaft. Applications de Havilland of Canada CV-73A Buffalo, 2xT64-GE- 10 (2,850 e.h.p.). Fiat G.222, 2XT64-GE-14 (3,060 e.h.p.). Grum man HU-16F Albatross, 2XT64 (2,850 e.h.p.). Kawasaki P2V-Kai, 2XT64-IHI-10 (2,850 e.h.p.). Shin Meiwa PX-S, 2xT64-IHI-10 (2,850 s.h.p.). (T64-GE-14) Similar configuration to T64-GE-12 but with non- integral forward-mounted gearbox. Take-off 3,060 e.h.p.; mass flow 24.51b/sec: pressure ratio 12.6:1: length 113in: width 29in: height 46in; weight 1,1301b. T58 Military free-turbine turboshaft. Extensively installed in USN and USAF helicopters. Joint development to higher ratings by GE and Rolls-Royce. Manufacture licensed to Rolls-Royce, Ishikawajima- Harima Heavy Industries, Alfa Romeo and Klockner-Humboldt- Deutz. Latest version is T58-GE-16 of 1.870 s.h.p. Applications Agusta Bell AB 204B, 1XT58-GE-3 (1,325 s.h.p.). Bell UH-1F, 1XT58-GE-3 (1,325 s.h.p.). Bell X-22A, 4XT58-GE-8D (1,250 s.h.p.). Boeing-Vertol CH-46A, 2XT58-GE-8B (1,250 s.h.p.). Boeing-Vertol CH-46D, 2XT58-GE-10 (1,400 s.h.p.). Boeing-Vertol CH-113 and CH-113A, 2XT58-GE-8B (1,250 s.h.p.). Kaman UH-2A, 1XT58-GE-8B (1,250 s.h.p.). Kaman UH-2C. 2XT58-GE-8B. Piasecki 16H-1C Pathfinder. 1XT58-GE-8B (1,250 s.h.p.). Sikorsky CH-3C. 2XT58-GE-1 (1,300 s.h.p.) or T58-GE-5 (1,500 s.h.p.). Sikorsky HH-3C, 2XT58-GE-1 (1.300 s.h.p.). Sikorsky HH-3E and CH-3E, 2XT58-GE-5 (1,500 s.h.p.). Sikorsky SH-3A and HH-52A, 2XT58-GE8B (1,250 s.h.p.). Sikorsky SH-3D, 2XT58-GE-10 (1,400 s.h.p.). (T58-GE-14) Ten-stage compressor, annular combustor, two-stage compressor-turbine, two-stage power-turbine. Rear-mounted integral gearbox. Take-off 1,600 s.h.p.; mass flow 13.71b/sec; pressure ratio 8.3:1: length 59in: width 18.8in; weight 4121b. General Electric Commercial Engine Division CF6 Civil twin-spool turbofan. Under development with GE corporate funding as prime powerplant for Douglas DC-10. Uses TF39 gas generator to energise new smaller diameter one and one-quarter-stage fan and new 1-p turbine. First engine ran in October 1968 and early achieved 45,7501b, 14 per cent above initial guaranteed rating. Scheduled for certification in mid-1970 and entry into service in late 1971. CF6, which is also being considered for the new BAC Three-Eleven and A-300B revised European airbus, has growth potential to 45,6001b by addition of two booster stages following fan i-stage. (Pratt & Whitney JT9D is alternative power- plant for DC-10.) Applications Douglas DC-10-10, 3XCF6-6 (40,0001b). Douglas DC-10-30, 3 X CF6-10 (45,6001b). (CF6-6) One and one-quarter-stage fan, 16-stage h-p compressor, annular combustor, two-stage h-p turbine, five-stage 1-p turbine. Take-off 40,0001b; b.p.r. 6.3:1; mass flow l,4501b/sec; pressure FLIGHT International, 2 January 1969 ratio 26:1: length I90in; maximum diameter 93.7in: weight 7,3501b. GE4/J5P Civil single-shaft augmented turbojet. Under joint FAA/GE funded development to power Boeing 2707-300. Testing of present Phase III version of GE4 started March 1968 and in September engine achieved 63,2001b, the highest thrust of any tur bine aero engine. Four ground-test and 16 flight test engines are involved: over 600hr testing have already been completed. First flight of Boeing SST is scheduled for March 1972 with entry into service following around 1977. Engine is closely based on J93 and J79 experience. (GE4/J5P) Nine-stage compressor, annular combustor. two-stage turbine. Close-coupled four-gutter afterburner, multi-flap primary and secondary variable ejector nozzles with integral noise sup pressor and thrust reverser. Take-off 50,5OOIb basic and 67,0001b with afterburning: mass flow 6331b/sec; pressure ratio 12.3:1; length 308in ; diameter 74in ; weight 11,0001b. Study Turbofan Civil twin-spool turbofan. A GE design study for 25,O00Ib engine to power Douglas DC-9 Series 50 project. Based on derated lower turbine temperature TF39 core engine but with by-pass reduced to 4:1. CF700 Civil free-turbine, aft-fan turbofan. Sole service example of turbofan for business jets, comprises aft-fan version of J85 military turbojet with scale version of CJ805-23 fan. Special constant-thrust, vertical-operating versions developed for hover rigs. (Military counterpart is TF37). Latest version is CF700-2D of 4,3501b. Applications Dassault Fan Jet Falcon, 2xCF700-2C (4,1251b). Dassault Falcon 70. 2XCF700-2D (4,3501b). (CF700-2C) Eight-stage compressor, annular combustor, two-stage compressor-turbine, single-stage fan turbine, single-stage aft-fan. Take-off 4,1251b; b.p.r. 1.9:1 ; mass flow (total) 1261b/sec: pressure ratio (gas generator) 7:1: length 53.6in: diameter 33.1in; weight 7251b. GI610 Civil single-shaft turbojet. Commercial version of J85 mili tary turbojet. Latest versions are the CJ610-8 and -9 of 3,1001b. Applications American Jet Industries T-610 Super Pinto, 1XCJ610-6 (2,9501b). Hansa HFB 320, 2XCJ610-1 (2,8501b). Lear Jet Model 23, 2XCJ610-1 (2,8501b) or CJ610-4 (2,8501b). Israel Aircraft Industries Jet Commander 1121A. 2XCJ610-1 (2,8501b). Israel Aircraft Industries Jet Commander 1121B and 1122. 2X CJ6IO-5 (2,9501b). Lear Jet Model 24, 2XCJ610-4 (2,8501b). Lear Jet Model 24B and 25, 2xCJ610-6 (2,9501b). (CJ610-6) Eight-stage compressor, annular combustor, two-stage turbine. Take-off 2,9501b; mass flow 441b/sec; pressure ratio 6.8:1 : length 45.4in; diameter I7.7in; weight 3921b. CJ805-23 Civil free-turbine, aft-fan turbofan. Sole example of air line aft-fan engine in service, has application only in Convair 990A. Comprises aft-fan version of CJ805-3 turbojet. (CJ805-23B) Seventeen-stage compressor, cannular combustor with ten flame tubes, three-stage compressor-turbine, single-stage fan turbine, single-stage aft-fan. Take-off I6,1001b; b.p.r. 1.47:1: mass flow (total) 4221b/sec; pressure ratio (gas generator) 13:1: length 149in: diameter 53in: weight 3,7661b. CI805-3B Civil single-shaft turbojet. Commercial version of J 79 military turbojet. Sole application, Convair 880-22M. (CJ805-3B) Seventeen-stage compressor, cannular combustor with ten flame tubes, three-stage turbine. Take-off 11,650; mass flow 171 lb/sec; pressure ratio 13:1; length 182; diameter 32in; weight 2,8171b. CT58 Civil free-turbine turboshaft. Commercial version of T58 military turboshaft. Is the only US helicopter turbine to enter airline service. Applications Sikorsky S-61L, 2XCT28-110 (1,250 s.h.p.) or CT58- 140 (1,400 s.h.p.). Sikorsky S-61N, 2XCT58-140 (1,400 s.h.p.). Sikorsky S-62A, 1XCT58-110 (1,250 s.h.p.). (CT58-140) Similar configuration to T58-GE-12 except for single- stage power-turbine. Take-off 1,400 s.h.p.; mass flow 13.7lb/sec: pressure ratio 8.3:1: length 59in: width 16.0in; weight 3401b. GLUSHENKOV USSR Turboshaft Only known example of an engine from this design bureau, this 900 e.h.p. turboshaft powers the Kamov Ka-25K multi purpose helicopter. Probably also installed in Ka-20 anti-submarine warfare helicopter. HINDUSTAN AERONAUTICS Bangalore, India HJE-2500 Military single-shaft turbojet. First example of Hindustan-designed and developed turbine engine. Intended application is production versions of Hindustan HJT-I6 Mk 2. (HJE-2500) Seven-stage compressor, cannular combusfor with seven flame tubes, single-stage turbine. Take-off 2,5001b; mass flow 45.21b/sec: pressure ratio 4.2:1 ; length 85in: diameter 26in; weight 5851b.
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