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Aviation History
1970
1970 - 0046.PDF
30 AERO ENGINES 1970 . . mounted gearbox. Take-off £70 s.h.p.; mass flow 9.5lb/sec: pressure ratio 5.2:1: length 71.46in: width 19.96in: height 24.68in: weight 2871b. TURBOMECA-SNECMA Turbomeca-Snecma GRTS (joint company of Turbomeca SA and Snecma). Headquarters: Paris, France Announced in March 1969, the company is the first of two new joint Turbomeca/Snecma companies (second is Groupement dTntent Economique Turbomeca-Snecma which see). Turbomeca-Snecma GRTS is responsible for the design development, manufacture, sales and service of the Larzac turbofan, joint venture of the twq parent concerns. M49 Larzac Civil and military two-shaft turbofan. First run in May 1969, three prototype engines are now on test. Intended mar ket is the business jet and military liaison and trainer aircraft. Flight standard engines are planned to be available by end of 1970 with flight testing occurring during 1971. Production engines are scheduled for delivery during 1972/73. Application Breguet / Dornier Alpha Jet project, 2 X Larzac. Das sault Mystere 10/Minifalcon, 2 X Larzac (2,3041b). Messerschmitt- Bolkow-Blohm/Nord Type 426 project, 2 x Larzac. Sud/Nord SN600 Corvette, 2 x Larzac. (M49 Larzac) Two-stage fan, four-stage h-p compressor, annular combustor, single-stage h-p and 1-p turbines. Take-off 2,3001b; b.p.r. 1.4:1; mass flow 57.31b/sec; pressure ratio 9:1; length 48.8in : diameter 17.3in; weight 5731b. TURBO-UNION Turbo-Union Ltd (joint company of Rolls-Royce Ltd, Motoren und Turbinen Union GmbH and Fiat SpA). Headquarters: London. England Formed in October 1969, the company has responsibility for management of the RB.199 engine programme for the Panavia MRCA-75. Shareholding by the three national companies is R-R. 40 per cent: MTU, 40 per cent; and Fiat, 20 per cent. RB.199 Military three-shaft augmented turbofan. Selected in com petition with the Pratt & Whitney JTF16 turbofan to power the Panavia MRCA-75 fighter, the RB.199 is a joint R-R/MTU/Fiat project with R-R's Bristol Engine Division as design and develop ment leader. Overall engine programme shares by the three com panies are respectively 32 per cent, 52 per cent and 16 per cent in proportion to the individual aircraft orders placed by the three countries. The contract covering the initial phase of development awarded to Turbo-Union by the NATO MRCA Development and Production Management Organisation in October 1969. Anticipated production contracts are likely to amount to around 3,000 engines worth over £600 million. Flight standard RB.199s are scheduled for delivery prior to May 1973 (first flight date for MRCA-75), with entry into service in 1975/76. Definitive version is 8,5001b RB.199- 34R giving 14,5001b with afterburning. Weight is about 1,8001b. UACL United Aircraft of Canada Ltd (subsidiary of United Aircraft Corporation). Headquarters: Longueuil, Quebec, Canada JT15D Civil two-shaft spool turbofan. First run September 1967 and flight tested under an Avro CF-100 in August 1968, the JT15D is intended to power business, transport and military aircraft in the 7,0001b to 12,5001b class. The gas generator section embodies component technology from the company's PT6 turboprop/turbo- shaft. Certification scheduled for November 1970, with production deliveries starting 1972. Growth version of 2,4001b planned for 1972 with further potential to over 3,0001b. Applications Beechcraft Fl commuter project, 3XJT15D. Beech- craft F2 commuter project, 4XJT15D. Cessna Model 500 Citation, 2XJT15D-1 (2,2001b). Dassault Mystere 10/Minifalcon. 2XJT15D-1 (2,2001b). Sud/Nord SN600 Corvette, 2XJT15D-1 (2,2001b). (JT15D) Single-stage fan, single-stage centrifugal h-p compressor, annular reverse-flow combustor. multi-stage h-p and 1-p turbines. Take-off 2,0001b: b.p.r. 3.3:1 : mass flow 73.lib/sec: pressure ratio 10:1: length 60.40in; width 27.55in; height 32.97in: weight 4801b. PT6A Civil and military free-turbine turboprop. Produced for a wide variety of applications, the PT6 (and industrial ST6) has been the sole UACL turbine prior to the advent of the JT15D. Unique by virtue of its "back-to-front" installation with the compressor fed via an integral plenum chamber. Over 2,500 engines built. Latest version is the 1,035 s.h.p. PT6A-50. Applications Air Parts Fletcher FU-1060, 1XPT6A-20 (500 s.h.p.). Beechcraft King Air A90 and VC-6A. 2XPT6A-20 (550 s.h.p.). Beechcraft Model 99 Airliner, 2XPT6A-20 (550 s.h.p.) or 2XPT6A- 27 (652 e.h.p.). Beechcraft King Air 100. 2XPT6A-28 (680 s.h.p.). FLIGHT International, I January 1970 Beechcraft Model 299 project. 2XPT6A-27 (652 e.p.h.), CASA C.212 Aviocar, 2XPT6A-27 (652 e.h.p.). Commuter Lines U-21A & NU-8F, 2XPT6A-20 (550 s.h.p.). de Havilland of Canada DHC-7, 4XPT6A-50 (1,035 s.h.p.). de Havilland of Canada Turbo-Beaver. 1XPT6A-6 (550 s.h.p.). de Havilland of Canada Twin Otter, 2X PT6A-20 (500 s.h.p.) or 2XPT6A-27 (652 e.h.p.). Dornier Dol32. 1XPT6A-20 (720 h.p.). EMBRAER C-95 Bandeirante, 2XPT6A-20 (500 s.h.p.) or 2XPT6A-27 (652 e.h.p.). Fairchild Hiller Heli-Porter, 1XPT6A-20 (500 s.h.p.) or 1XPT6A-27 (652 e.h.p.). General Air craft GAC-100, 4XPT6A-40 (894 e.h.p.). Helio Stallion, 1XPT6A- 27 (680 s.h.p.). Israel Aircraft Industries Arava, 2XPT6A-27 (620 s.h.p.). McKinnon Goose, 2XPT6A-20 (550 s.h.p.). McKinnon/ Grumman Mallard, 2XPT6A-27 (652 e.h.p.). Pacific Airmotive PAC-1, 1XPT6A. Piper PA-31T Turboprop Navajo, 1XPT6A-27 (680 s.h,p.). Saunders ST-17, 2XPT6A-27 (715 e.h.p.). Swearingen Merlin IIA, 2XPT6A-20 (550 s.h.p.) or PT6A-27 (625 e.h.p.). Vickers/Slingsby Cameo V-liner project, 2XPT6A-27. (PT6A-27) Three-stage axial plus single-stage centrifugal compres sor, annular reverse-flow combustor, single-stage compressor-turbine, single-stage power-turbine. Integral front-mounted gearbox. Take-off 652 s.h.p.; mass flow 6.61b/sec: pressure ratio 7:1; length 62in; diameter 19in; weight 2891b. PT6B Civil free-turbine turboshaft. Turboshaft counterpart to PT6A turboprop. Applications Berlin Doman Helicopter project, PT6B-10C. Lock heed XH-51A, 1XPT6B-9 (550 s.h.p.). Lockheed Model 286, IX PT6B-9 (550 s.h.p.). Nord 511, 1XPT6B-16. (PT6B-9) Similar in configuration to PT6A but with single-stage reduction gear in place of two-stage. Take-off 550 s.h.p. Intended for business and light twin jet transport aircraft, the UACL JTISD turbofan is rated at 2,0001b but growth versions may eventually reach more than 3,0001b take-off thrust T74 Military free-turbine turboshaft. Military counterpart to PT6A turboprop. Experimental installation in North American OV-10A. PT6T Turbo "Twin Pac" Civil coupled free-turbine turboshaft. Coupled PT6B turboshaft with integral front-mounted gearbox, now entering production for Bell Model 212 Twin Jet as 1,800 s.h.p. PT6T-3. Also has possible application in SIAI-Marchetti SV-20. T400 Military coupled free-turbine turboshaft. Military counter part to PT6T Turbo "Twin Pac." entering production for US Navy helicopters. Applications Bell AH-U HueyCobra and CUH-1N Twin Cobra, 1XPT6T-4 (1,800 s.h.p.). Kaman Sealite. 1X T400-CP-480 (1,800 s.h.p.). WILLIAMS RESEARCH Williams Research Corporation. Headquarters: Walled Lake. Michigan. USA Specialises in the development and manufacture of small gas tur bines including WR-9, WR-19, WR-24 and T-400. Applications include Canadair CL-89 AN/USD-501 surveillance and reconnais sance drone, and Bell Aerosystems Jet Flying Belt with WR-19 turbofan. The company is also competing with Continental and Rover to power the projected flying ejector seats being studied by Kaman and Stratos-Western on behalf of the US Navy.
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