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Aviation History
1970
1970 - 0043.PDF
FLIGHT International, I January 1970 (Olympus Mk 301) Six-stage 1-p compressor, seven-stage h-p com pressor, cannular combustor with ten flame tubes, single-stage h-p turbine, single-stage 1-p turbine. Take-off 20,0001b; mass flow 2901b/ sec; pressure ratio 13:1: length 131in: diameter 44.5in: weight 4,290lb. Viper Civil and military single-shaft turbojet. More than 3,000 Vipers ordered and over 2,000 delivered to 30 or more countries for air forces and executive operators. Latest version is 3,7501b Viper 600, uprated to 4,0001b for military applications. Manufacture licensed to Piaggio (extended to Viper 500 in March 1969), Hin dustan Aeronautics, Atlas Aircraft and Commonwealth Aircraft with assembly arrangement also with Yugoslav Government. In July 1969 agreement signed with Fiat for technical collaboration in design, development and manufacture of Viper 600. Joint pro duction planned for 1971. Applications Aermacchi MB.326 A, B, D, F & H, IX Viper II Mk 22/1 (2,5001b): MB.326G, GB & K, IXViper 20F-20 Mk 540 (3,410). Atlas Aircraft Impala, lXViper. BAC Jet Provost T.3, IX Viper 8 Mk 102 (1,7501b); Jet Provost T.4 & T.5/BAC.145, 1 XViper 11 Mk 202 (2,5001b): BAC.167 Strikemaster, lx Viper 20F-20 Mk 535 (3,4101b). GAF Jindivik Mk 103A, lXViper 11 Mk 201 (2,5001b). Hawker Siddeley HS.125 Series 1, 2 X Viper 520 (3,0001b); HS.125 Series 1A & IB, 2xViper 521 (3,1301b) or Viper 522 (3,3601b): HS.125 Series 2/Dominie T.l, 2xViper 520 (3,0001b): HS.125 Series 3A, 3AR & 3B, 2 X Viper 522 (3,4101b). Hawker Siddeley Shackleton MR.3 Phase 3, 2 X Viper 11 Mk 203 (2,7001b). Hindustan HJT-16 Kiran, lxViper 11 Mk 22/8 (2,5001b). Piaggio PD.808, 2xViper 526 (3,4101b). SOK.O G2-A Galeb, lXViper 11 Mk 22/6 (2,5001b). SOKO Jastreb, 1 xViper Mk 531 (3,1301b). (Viper 600) Eight-stage compressor, annular combustor, two-stage turbine. Take-off 3,7501b and 0.9361b/lb/hr: mass'flow 58.41b/sec; pressure ratio 5.8:1 : length 64.6in: diameter 24.5in : weight 7601b. Orpheus Military single-shaft turbojet. In addition to R-R manu facture, has been licence-built by Fiat, Klockner-Humboldt-Deutz and Hindustan Aeronautics. Also is 5,7501b Orpheus 502 boost unit, first run February 1968. for potential application in civil and military transports. Applications Fairchild C-119G, lx Orpheus 701 (4,7001b). Fiat G.91, G.91R/1. G.91R/4 & G.91T, IXOrpheus 80302 (5,0001b): Fiat G.91R/3 & G.91T/3, lxOrpheus 803D Hll (5.0001b). Fuji TF1-2, lxOrpheus 805 (4,0001b). Hawker Siddeley Gnat Mk 1, lxOrpheus 701 (4,7001b): Hawker Siddeley Gnat T.l, IXOrpheus 101 (4,5201b). (Orpheus 803) Seven-stage compressor, cannular combustor with seven flame tubes, single-stage turbine. Take-off 5,0001b: mass flow 841b/sec; pressure ratio 4.14:1: length 96.1in: diameter 32.4in: weight 9001b. Small Engine Division. Headquarters: Leavesden, near Watford, England In addition to the products listed below, the Division is the main Two Rolls-Royce Turbomeca RB.I72/T.260 Adour turbofans power the Breguet/BAC Jaguar. Each has a take-off thrust of 4,6201b basic and 6,9451b with afterburner distributor for Allison Model 250 turboprop and turboshaft engines for the UK and other countries outside North America. More than 260 Model 250s have already been supplied, overhauls are under way and preparations are being made for manufacture. The Division is also licensed to manufacture the US General Electric T64 turbo prop and turboshaft engines, has collaborated with Klockner- Humboldt-Deutz in joint development of the T112 APU for the VFW VAK 191B, and is participating in the manufacture of Turbomeca Astazou and Turmo turboshafts for the Sud-Aviation SA.341 and SA.330 under the Anglo-French helicopter programme. Gyron Junior Military single-shaft turbojet. Sole application is Hawker Siddeley Buccaneer S.l. (Gyron Junior Mk 101) Eight-stage compressor, annular combustor. two-stage turbine. Take-off 7,1001b; mass flow 1201b/sec; pressure ratio 6:1; length 121.lin; diameter 32.3in ; weight 2,1001b. BS.360 Military two-shaft free-turbine turboshaft. First run Sep tember 1969, BS.360 is being developed under MinTech contract to power Westland WG.13 as part of the Anglo-French helicopter programme. Designed as a compact, lightweight, high-performance engine using unusual two-shaft free-turbine layout to provide high pressure ratio, low s.f.c. turboshaft easy to maintain in the field. Will be first Division design of engine to be built since Gyron Junior Is. Designated RS.360 for later applications, including West- land WE-01 project with four 360s. (BS.360-07) Four-stage 1-p compressor (driven by i-p turbine), single-stage centrifugal h-p compressor, annular reverse-flow com- bustor, single-stage h-p and i-p turbines, two-stage 1-p power turbine. Max. contingency power (2Jmin) 900 s.h.p.; max. power (lhr) 830 s.h.p.; pressure ratio 12.15:1; length 43in: height 22in: width 22in : weight 3001b. Gnome Civil and military free-turbine turboshaft. Licence-built Anglicised version of General Electric T58, also sub-licensed to Alfa-Romeo. Joint development by R-R and GE to higher ratings. Latest version is 1,750 s.h.p. Gnome H1800 with increased mass flow, zero-stage compressor and two-stage power turbine. More than 1,100 Gnomes in service have accumulated well over 500.000hr flying. Applications Agusta A101G, 3xGnome H1400 (1,500 s.h.p.). Agusta A101H, 3 X Gnome H1800 (1.750 sJi.p.). Agusta Twin 205. 2xGnome H1200 (1,250 s.h.p.). Agusta-Bell AB204B. lxGnome H1000 (1.050 s.h.p.) or Gnome H1200 (1,250 s.h.p.). Boeing-Vertol HKP-4, 2 x Gnome H1200 (1,250 s.h.p.). Westland Sea King HAS1. 2xGnome H1400 (1,500 s.h.p.). Westland Whirlwind 3, 9, 10 & 12. ix Gnome H1000 (1,050 s.h.p.). (Gnome HI400) Ten-stage compressor, annula combustor, two- stage compressor-turbine, single-stage power-turbine. Integral rear- mounted gearbox. Take-off (5min) 1,500 s.h.p.; length 54.8in: width 22.7in : height 21.6in: weight 3321b. Coupled Gnome Civil and military coupled free-turbine turbo shaft. Comprises two Gnome engines coupled by common gearbox to provide single output drive. Applications Westland Wessex 2. 5. 51 & 60. lx Coupled Gnome H1200 (de-rated to 1,550 s.h.p,). (Coupled Gnome H1200) Configuration similar to Gnome H1400 but with rear-mounted coupling gearbox. Maximum potential power 2,500 s.h.p. Nimbus Military free-turbine turboshaft. Based on Turbomeca gas generator technology. Sole applications are Westland Scout and Wasp with respectively lxNimbus Mk 105/502 (685 s.h.p.) and IX Nimbus Mk 103/503 (710 s.h.p.).. (Nimbus .Mk 103/503) Two-stage axial plus single-stage centrifugal compressor, annular combustor two-stage compressor-turbine, single- stage power-turbine. Integral rear-mounted gearbox. Take-off (5min) 710 s.h.p., ISA +25°C: mass flow HOlb/sec: pressure ratio 6.5:1: length 7,317in; width 38.7in; height 33.6in; weight 3901b. ROLLS-ROYCE TURBOMECA Rolls-Royce Turbomeca Ltd (joint company of Rolls-Royce Ltd and Turbomeca SA). Headquarters: London, England. The company was formed in June 1966 by R-R and Turbomeca to manage the development and manufacturing programmes for the Adour turbofan. RB.172/T.260 Adour Military two-shaft augmented turbofan. First run at Derby in May 1967, the Adour is the subject of an Anglo/ French governmental agreement for joint Rolls-Royce/Turbomeca development of an engine to power the Breguet/BAC Jaguar (which first flew on September 8, 1968). R-R is responsible for the combustion system, turbine and afterburner, Turbomeca having authority for the fan. compressors and external wheelcase. Snecma is also participating in manufacture of the afterburner. Joint manu facture of the Adour for the 400 Jaguars on order is planned to start early this year, building up to large numbers in 1971 when the aircraft enters service. Ishikawajima-Harima Heavy Industries is likely to undertake licensed manufacture for Japanese applications. Applications BAC/Commonwealth Aircraft AA-107 project. 1X
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