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Aviation History
1968
1968 - 0019.PDF
FLIGHT International, 4 January 1968 AERO ENGINES 1968 .. . cooling for stator and rotor blading for first two stages of turbine. Applications Grumman E-2A Hawkeye, 2XT56-A-8 (4,050 e.h.p.). Lockheed C-130A Hercules, 4xT56-A-9 (3,750 e.h.p.); C-130B & E, 4XT56-A-7 (4,050 e.h.p.); C-130H, HC-130H & C-130K, 4XT56-A-15 (4,910 e.h.p.). Lockheed P-3A Orion, 4XT56-A-10W (4,500 e.h.p.); P-3B Orion, 4XT56-A-14 (4,910 e.h.p.). (T56-A-15) Fourteen-stage compressor, cannular combustor with six flame tubes, four-stage turbine. Non-integral front-mounted gearbox. Take-off 4,910 e.h.p.; mass flow 32.41b/sec; pressure ratio 9.25:1; length 146in; width 27in; height 39in; weight 1,8251b. Model 501 Civil single-shaft turboprop. Commercial counterpart of T56, is sole US turboprop to enter airline operation. Applications Convair CV-580, 2X501-D13D (3,750 e.h.p.). Lock- heed 188A Electra, 4X501-D13 (3,750 e.h.p.). Lockheed 100 Hercules, 4X501-D22 (4,050 e.h.p.). (Model 501-D22) Configuration similar to T56. Take-off 4,050 e.h.p.; length 146in; width 27in; height 39in; weight 1,8351b. ALVIS ROVER Alvis Ltd, subsidiary of the Rover Company, Coventry, England Wolston Civil single-shaft turboprop. Conversion of Rover indus- trial turbine, flying in Chipmunk with installation by Hants & Sussex Aviation. (Wolston) Single-stage centrifugal compressor, tubular reverse-flow combustor with single flame tube, single-stage axial turbine. Integral front-mounted gearbox. Maximum continuous rating 107 s.h.p., weight 1401b. BOEING (Turbine Division, The Boeing Company), Seattle, Washington, USA Model 502/T50 Military free-turbine turboshaft. Sole propulsion role is powering Gyrodyne QH-50C US Navy drone helicopter. Model 502-10VC/T50-BO-8A Single-stage centrifugal compressor, two-can straight-through flow combustor, single-stage compressor- turbine, single-stage power-turbine. Integral rear-mounted gearbox. Military rating 300 s.h.p.; mass flow 4.221b/sec; pressure ratio 4.63:1; length 40.48in; width 43.52in; height 28.15in; weight 3341b. Model 550/T50 Military free-turbine turboshaft. Improved deriva- tive of Model 502. Powers Gyrodyne QH-50D drone helicopter. (Model 550-1/T50-BO-12) Single-stage axial plus single-stage centrifugal compressor, two-can reverse-flow combustor, single-stage compressor-turbine, single-stage power-turbine. Integral rear-mounted gearbox. Maxium rating 365 s.h.p.; mass flow 4.41b/sec; pressure ratio 5.8:1; length 37.5in; width 40.24in; height 22.5in; weight 2671b. BRISTOL SIDDELEY-see under Rolls-Royce CONTINENTAL (Gas Turbine Division, Continental Aviation and Engineering Corporation), Detroit, Michigan, USA T67 Military coupled free-turbine turboshaft. Comprises two T72 engines coupled by common gearbox to provide single output drive. Applications Agusta A109B, 1XT67-T-1 (1,540 s.h.p.). Bell Model 208, 1XXT67-T-1 (1,480 s.h.p.). (T67-T-1) Two-stage axial plus single-stage centrifugal compressor, annular combustor, two-stage compressor turbine, single-stage power-turbine. Integral front-mounted coupling gearbox. Maximum power 1,540 s.h.p.: mass flow 6.851b/sec; pressure ratio 7.7:1; length 53in ; width 38in ; weight 5191b. J69 Military single-shaft turbojet. Based on Turbomeca Marbore, has both drone and manned aircraft applications. Latest version is J69-T-41A (1,9201b). Applications Cessna T-37A, 2xJ69-T-9 (9201b). Cessna T-37B & T-37C, 2xJ69-T-25 (1,0251b). Ryan BQM-34A Firebee, lxJ69-T-29 (1,7001b); BQM-34E Firebee II, 1XJ69-T-6 (1,8401b). DAIMLER-BENZ Stuttgart-Untertiirkheim, West Germany DB 721 (PTL10) Civil & military free-turbine turboshaft. Under development in both turboshaft and turboprop forms. Latest version being developed at 2,400 e.h.p. Supported by government finance. (DB 721) Eight-stage compressor, annular combustor, two-stage compressor-turbine, single-stage power-turbine. Non-integral front- mounted gearbox. Take-off 2,200 e.h.p.; mass flow 221b/sec: pressure ratio 6:1; length 91.3in; diameter 19.1in; weight 5501b. DB 730 (ZTL6) Civil & military free-turbine aft-fan turbofan. Uses DB 720 as gas generator with DB 721 compressor first-stage as aft-fan. Under development as Daimler-Benz private venture. (DB 730F) Four-stage axial plus single-stage centrifugal compressor, 21 annular combustor, two-stage compressor-turbine, single-stage fan- turbine, single-stage aft-fan. Take-off 2,2501b & 0.441b/lb/hr; b.p.r 5.5:1; mass flow (total) 81.61b/sec; pressure ratio (gas generator) 5.5:1 (fan) 1.295:1; length 88.6in; diameter 20.3in. FLYGMOTOR (Svenska Flygmotor), Trollhdtan, Sweden RM8 Military twin-spool augmented turbofan. Licensed version of Pratt & Whitney JT8D-22 civil turbofan, is being developed by Flygmotor as supersonic afterburning engine for SAAB 37 Viggen Mach 2 intercepter and strike fighter. (RM8) Two-stage fan plus four stage i.p. compressor (both driven by I.p. turbine), seven-stage h.p. compressor, cannular combustor with nine flame tubes, single-stage h.p. turbine, three-stage I.p. turbine. Flygmotor afterburner, multi-flap variable primary nozzle with ejector, three-petal thrust reverser, fixed-area secondary nozzle. Take-off 16,0001b basic, 26,4501b with afterburning; b.p.r. 1:1; mass flow 3201b/sec; pressure ratio (overall) 16.5:1; length 118.lin; diameter 55.lin; weight 4,6301b. GENERAL ELECTRIC (Aircraft Engine Group, General Electric Company, West Lynn, Massachusetts, USA CF6/34 Civil twin-spool turbofan. Uses TF39 gas generator with new smaller diameter one and one-quarter-stage fan and new I.p. turbine. Proposed by GE for Lockheed L-1011 and Douglas DC-10 airbus projects in competition with Pratt & Whitney JT18D and Rolls-Royce RB211 (CF6/34) One and one-quarter-stage fan, 16-stage h.p. compressor, annular combustor, two-stage h.p. turbine, five-stage l.p. turbine. Take-off 34,0001b; BPR 6:1; mass flow 1,3801b/sec; pressure ratio (overall) 25:1; length 172in; diameter 89in; weight 6,9751b. GE Military turboshaft. Demonstrator engine being built under contract to US Army for new 1,500 s.h.p. turboshaft for helicopter and V/STOL aircraft. Designed to provide improved performance capabilities coupled with rugged simplicity for field operation. Competing with Pratt & Whitney ST9 in two-year programme. TF34 Military twin-spool turbofan. Competing with Allison TF32 as power unit for US Navy's VSX anti-submarine warfare project. Is a high b.p.r. turbofan, no doubt related to TF39 technology. TF34-GE-2 is rated at between 7,0001b and 8,0001b. GE1/10 Military twin-spool augmented turbofan. Comprises GE1 gas generator with moderate b.p.r. fan, afterburner and thrust- vectoring device. Performance classified, but length is 143in and diameter 38in. This is GE entry for USAF AMSA and US/FRG AVS projects, and is in competition with Pratt & Whitney JTF16. Thrust-vectoring device of swivel-nozzle type recently successfully tested for GE1/10 by MAN-Turbo under contract to GE. GE1/J1A1 Military single-shaft turbojet. Utilising GE1 gas generator with the addition of an afterburner, provides turbojet for new advanced performance supersonic fighters and intercepters in 7,0001b class. Length and diameter: approximately 140in and 24in. Vapcom Military variable-pumping gas generator. A feasibility study for a turbine unit with a variable pumping compressor, under contract awarded by USAF Aero-Propulsion Laboratory. Is part of Air Force's Project Forecast on long-range technical planning, and marks step forward in the variable-cycle engine which automatically modifies its configuration to suit change in flight regime. GE4/J5 Civil single-shaft augmented turbojet. Selected in December 1966 to power the Boeing 2707 SST, the GE4 is in Phase HI of its development programme. Four ground-test and 16 flight test engines are involved, with the first fully operational, non-certificated engine to be delivered to Boeing in December 1969. Testing of the new increased-capacity compressor started in November last year. Engine configuration 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 suppres- sor and thrust reverser. Take-off 49,1001b basic and 63,2001b with afterburning; mass flow 6201b/sec; medium pressure ratio; length 308in; diameter 74.2in; weight approximately 10,5001b. TF39 Military twin-spool turbofan. Under development to power the Lockheed C-5A Galaxy, the TF39 is financed under USAF programme to $459 million covering supply of 258 engines. First four flight-qualified YTF39s scheduled for delivery to Lockheed last month, and a further 20 to be delivered by June 1968. Delivery of early operational TF39s planned for September. Major design features include record 8:1 b.p.r. and use of unique one and one- half stage fan with tip-shrouded half-height blades located ahead of fan blades. Engine configuration based on GE1/6 scale version. (TF39) One and one-half stage fan, 16-stage h.p. compressor, annular combustor, two-stage h.p. turbine, five-stage l.p. turbine. Take-off 41.1001b; b.p.r. 8:1; mass flow l,5491b/sec; pressure ratio, (overall) 25:1; length 324in; diameter lOOin; weight 7,2151b,
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