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Aviation History
1969
1969 - 0031.PDF
FLIGHT International, 2 January 1969 Applications Aero Commander Turbo Commander 11, 2XTPE33I- 43BL(605 e.h.p.) Air Parts Fletcher FU-1160, 1 XTPE331 (530 s.h.p.). CASA/HFB CASA-212 Aviocar, 2XTPE331-201 (715 s.h.p.). Car- stedt Jet Liner 600, 2XTPE331-100 (665 e.h.p.). Conroy Stolifter. 1XTPE331-25A (605 e.h.p.). de Havilland of Canada DHC-7. 4XTPE331-3O0 (800 s.h.p.). de Havilland of Canada DHC-2 Turbo- Beaver, 1XTPE331 (575 s.h.p.). Fairchild Hiller Heli-Porter PC-6/ C-H2, 2XTPE331-25D (575 s.h.p.). Handley Page C-10A Jetstream 3M, 2XTPE331-301W (895 e.h.p.). Mooney/Mitsubishi MU-2A and -2E, 2xTPE331-25A (605 e.h.p.). Mooney/Mitsubishi MU-2F, 2XTPE331-151A (705 e.h.p.). Saab 1017, 4XTPE331-201 (715 s.h.p.). Short Skyvan Srs 3, 2XTPE331-20I (715 e.h.p.). Swearingen Metro Commuter, 2XTPE331-303 (895 e.h.p.). Swearingen Merlin TIB, 2XTPE331-151G (665 e.h.p.). Volpar Super Turbo 18. 2XTPE331-47 (575 s.h.p.). Volpar Turboliner, 2XTPE331-151 (715 e.h.p.). (TPE331-201) Two-stage (single-sided) centrifugal compressor, annular reverse-flow combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 750 e.h.p.: length 46.01in: width 2l.l8in: height 26.46in ; weight 3361b. T76 Military single-shaft turboprop. Derived from TPE331 with application in the North American OV-10A Bronco. T76-G-10 and -12 are similar to TPE331-201 with the same ratings but are handed for opposite rotation. TSE36 Civil single-shaft turboshaft. Derived from AiResearch GTP36-7 APU. A new private venture development aimed at replacing piston engines in the 150 s.h.p. to 250 s.h.p. range. Certification is scheduled for February this year. Applications Enstrom F-28A (FTB), 1XTSE36-1 (220 s.h.p.). Enstrom T-28, 1XTSE36-1 (220 s.h.p.). Hughes 269A (FTB), 1XTSE36-1 (220 s.h.p.). Verticraft VC 1, 2XTSE36-1 (220 s.h.p.) driving tip jet compressor. (TSE36-1) Single-stage (single-sided) centrifugal compressor, single- can torus combustor, single-stage (single-sided) radial inflow turbine. Non-integral gearbox. Take-off 220 s.h.p.: weight approximately 1651b. ALLISON Allison Division. General Motors Corporation). Indianapolis. Indiana. USA TF32 Military twin-spool turbofan. Unsuccessful entrant in USN's VSX engine competition. TF4I Military twin-spool turbofan. An advanced derivative of Rolls-Royce RB.168-25 (designated RB.168-62), the TF41 is subject of $227.3 million USAF contract awarded jointly to Allison and R-R for development and production of 500 engines to power LTV A-7D Corsair II in place of Pratt & Whitney TF30. Deliveries started in June 1968 and in July and December the USN awarded Allison further contracts amounting to $43 million to develop higher rated version for Navy A-7Es. R-R is principal sub-contractor. Applications LTV A-7D Corsair II, 2XTF41-A-1 (14,2501b). LTV A-7E Corsair II, 2XTF41-A-2 (15,0001b). (TF41-A-1) Three-stage 1-p compressor and two-stage i-p compressor (both driven by 1-p turbine),, 11-stage h-p compressor, cannular combustor with ten flame tubes, two-stage h-p and 1-p turbines. Take-off 14,2501b: b.p.r. 0.77:1: mass flow 2581b/sec: pressure ratio 20 :1 overall. Quiet Engine Civil three-shaft turbofan. Allison and Pratt & Whitney submitted prototype engine design proposals to the NASA in November last year as part of the Administration's Quiet Engine Program on which it plans to spend about $10 million annually for the next five years. Basic aim of the programme is to produce engines capable of operating at a noise level at least 15 to 20 decibels lower than the P&W JT3D. A contract for construction of two engines is to be awarded early this year. Rolls-Royce is sub-contractor to Allison for its quiet engine studies. Potential applications All Boeing 707/720 series and Douglas DC-8 series aircraft. (Allison Quiet Engine) Single-stage fan, eight-stage i-p compressor, eight-stage h-p compressor, annular combustor, single-stage h-p and i-p turbines, five-stage 1-p turbine. Take-off 22,0001b: b.p.r. 5:5:1 : pressure ratio approximately 24:1: length 153in: diameter 74in: weight approximately 4,8001b. GMA-100 Civil/military core engine. An advanced technology gas generator being developed as a building-block engine with 651b/sec mass flow. As the core engine for future Allison turbofans, the GMA-100 has potential up to thrusts of 20,0001b for a b.p.r. of 5 :1. T80 Military free-turbine turboshaft. An advanced lightweight turboshaft demonstrator of low s.f.c. in the 5,000 to 6,000 s.h.p. category being developed under USN contract. Essentially a non- regenerative version of the erstwhile Allison T78 regenerative turboprop, the T80 features a high pressure ratio compressor, cooled turbine and low-speed free-turbine obviating need for reduc tion gearing. Following component testing, a demonstrator was scheduled to run mid-1968 under designation T80-A-2. Model 250 Civil free-turbine turboshaft. Leading US low-power helicopter turbine, is a commercial counterpart to the T63 military turboshaft. Development uprating to 400 s.h.p. in both turboshaft and turboprop forms was announced in September 1968 (replacing originally proposed 370 s.h.p. series). FAA certification of these versions is expected by December this year and deliveries should start in February 1970. Production capacity for 317 s.h.p. models is being doubled to 250 engines per month. Rolls-Royce is sales and service distributor in Europe, Africa, South America, the Middle East and Far East, and Hawker de Ha.villand (Australia) has similar franchise for South Pacific. R-R also holds option for exclusive licence for manufacture in UK.. Applications Agusta Model I09C, 2x250-04 (370 s.h.p.). Agusta Bell 206A JetRanger, 1X250-C18A (317 s.h.p.). Bell 206A JetRanger. 1X250-C18 (317 s.h.p.). Berlin Doman BD-68, 3x250-04 (370 s.h.p.). Bolkow Bo 105. 2X250-O8 (317 s.h.p.). Fairchild Hiller FH-1100, 1x250-08 (317 s.h.p.). Filper Research Beta 300. 1x250-09 (317 s.h.p.). Hughes 500 and 500U, 1x250-08 (252 s.h.p.). Nord 500, 2x250-08 (317 s.h.p.). (Model 250-C20) Six-stage axial plus single-stage (single-sided) centrifugal compressor, annular reverse-flow combustor, two-stage compressor turbine two-stage power-turbine. Ventral-mounted integral gearbox. Take-off 400 s.h.p.: length 40.3in: width I9in: height 22.5in : weight 1551b. Model 250 Civil free-turbine turboprop. Propeller-driving version of Model 250 turboshaft. Production deliveries of 250-B15 (317 s.h.p.) were scheduled for late 1968. Applications Cessna 0-2T, 1X250-B15G (317 s.h.p.). Cessna 0-2TT, 1X250-B17 (400 s.h.p.). Helio H-634T Twin Stallion. 2X250-B15 (317 s.h.p.). Robertson STOL series. (Model 250-B17) Configuration similar to Model 250-C20 except for larger dorsal-mounted gearbox. Take-off 400 s.h.p.: length 44.6in: width 19in : height 22.5in : weight 1921b. T63 Military free-turbine turboshaft. Military counterpart to civil Model 250. Major production programme for US Army light observation helicopter involving several thousand engines. Specialist development of regenerative version, Model 250-E3, on behalf of US Army, flight demonstrated in Hughes YOH-6A. Applications Bell OH-58A and TH-57A JetRangers, 1 X T63-A-5A (252.5 s.h.p.). Hughes OH-6A Cayuse. 1XT63-A-5A (252.5 s.h.p.). Mississippi State University XV-11A, 1XT63-A-5A (250 s.h.p.) for propeller drive and b.l.c. suction. Westland WE-01. 2x coupled T63. (T63-A-5A) Configuration and dimensions similar to Model 250-C20. Take-oft 317 s.h.p. at s.l. and 59°F. Weight 1391b. T56 Military single-shaft turboprop. Sole US high power turboprop to be produced in quantity and progressively developed. As T56-A- 15, was first American engine to enter service with air-cooled tur bine blading. Latest development version is smaller, lighter, with 5,325 e.h.p. T56-A-18 operating at higher turbine temperature. New features include annular combustor, advanced fuel system and air- cooling for stator and rotor blading for first two stages of turbine. Applications Aero Spacelines Guppy and Super Guppy, 4xT56. 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-l5 (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.), Lockheed YP-3C Orion. 4xT56. (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 Her cules, 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 British Leyland Motor Corporation). Coventry. England. TJ125 Minijet Military single-shaft turbojet. Built under licence from Rover Gas Turbines Ltd (subsidiary of British Leyland) to power the Belgian MBLE Epervier surveillance drone. The Minijet is a two-speed engine with double-datum governor to reduce speed ahead of radio-controlled landing of Epervier with cameras and film intact. (TJ125 Minijet) Single-stage (single-sided) centrifugal compressor. annular combustor, single-stage (single-sided) radial inflow turbine. Take-off and maximum continuous 1141b: mass flow 2.051b/sec: pressure ratio 3.9:1: length approximately 12in: width 10.5in; height 11.85in; weight 431b.
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