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Aviation History
1968
1968 - 0026.PDF
28 FLIGHT International, 4 January 1968 Shortly to begin its operational association with Concorde, the Rolls- Royce Bristol Engine Division's Olympus 593 is derived from a military background AERO ENGINES 1968... RB.90 Avon 200 Military single-shaft augmented turbojet. Major military version of the Avon. License manufactured by Fabrique Nationale, and by Flygmotor as RM5 with Swedish afterburner to power Saab Lansen. Applications BAC Canberra Mk 9, 2 X Avon RA.24 Mk 206 (11,2501b). BAC Lightning F2, 3 & 5, 2xAvon RA.24R Mk 210 (11,2501b, or 14,3701b with afterburning). BAC Scimitar Fl, 2 X Avon RA.24 Mk 202 (11,2501b). Hawker Siddeley Hunter Mks 9, 10 & 12, lxAvon RA.28 Mk 207 (10,1501b). Hawker Siddeley Sea Vixen FAW2, 2 x Avon RA.24 Mk 208 (11,2501b). (RB.90 Avon RA.28 Mk 208) Fifteen-stage compressor, cannular combustor, two-stage turbine. Take-off 11,2501b; length 126.9in; diameter 28in. Dart Civil and military single-shaft turboprop. Outstandingly success- ful turboprop, still in quantity production since starting in 1953. Applications BAC Project 201, 2 x Dart RDa.7 (2,230 e.h.p.), BAC Viscount 700, 4xDart RDa.6 Mk 510 (1,670 e.h.p.). BAC Viscount 800, 4xDart RDa.6 Mk 510 (1,670 e.h.p.), or Dart RDa.7 Mk 520 (1,815 e.h.p.), or Dart RDa.7/1 Mk 525F (1,910 e.h.p.), or Dart RDa.7/2 Mk 530 (2,020 e.h.p.). Breguet 1050 Alize, IX Dart RDa.7 Mk 21 (2,020 e.h.p.). Convair 600/640, 2 x Dart RDa.10 Mk 542-4 (3,025 e.p.h.). Fairchild Hiller F-27, 2 X Dart RDa.6 Mk 511 (1,670 e.h.p.). Fairchild Hiller F-27A & F, 2 x Dart RDa.7 Mk 528-7E (2,105 e.h.p.). Fairchild Hiller F-27B, 2 X Dart RDa.6 Mk 514-7 (1,850 e.h.p.). Fairchild Hiller F-27J, F-227 & F-227B, 2 x Dart RDa.7 Mk 532-7 (2,250 e.h.p.). Fokker F.27 Series 100 & 300. 2 x Dart RDa.6 Mk 517-7 (1,850 e.h.p.). Fokker F.27 Series 200, 400 & 500, 2 x Dart RDa.7 Mk 532-7 (2,255 e.h.p.). Grumman Gulfstream I. 2XDart RDa.7/2 Mk 529-8 and E (2,100 e.h.p.). Handley Page Herald Series 100, 2xDart RDa.7/2 Mk 526 (2,020 e.h.p.). Handley Page Herald Series 200, 2xDart RDa.7/2 Mk 527 (2,105 e.h.p.). Hawker Siddeley Argosy 220, 4 X Dart RDa.7/2 Mk 532/1 (2,230 e.h.p.). Hawker Siddeley Argosy C Mk 1, 4 x Dart RDa.8 Mk 101 (2,690 e.h.p. with water methanol). Hawker Siddeley 748 Series 1, 2xDart RDa.6 Mk 514 (1,860 e.h.p.). Hawker Siddeley 748 Series 2, 2XDart RDa.7/2 Mk 530 or 531 (2,020 e.h.p.). Hawker Siddeley Andover C Mk 1, 2 X Dart RDa.12 Mk 201 (3,245 e.h.p.). NAMC YS-11 and YS-11A, 2xDart RDa.10 Mk 542-10 (3,025 e.h.p.). (Dart RDa.10 Mk 542) Two-stage centrifugal compressor, tubular combustor with seven flame tubes, three-stage turbine. Take-off 3,025 e.h.p.; mass flow 271b/sec; pressure ratio 6.3:1; length 98in; diameter 38in; weight 1,3371b. Rolls-Royce Bristol Engine Division, Bristol BS.360 Military free-turbine turboshaft. A new design of turbo- shaft embodying Rolls-Royce technology and chosen to power the twin-engined Westland WG 13 under the Anglo-French helicopter agreement signed in October 1967. The BS.360-07 for the WG 13 is flat rated at 850 s.h.p. Modular construction is used to facilitate main component replacement. BS.358 Civil and military twin-spool turbofan. Announced in Sep- tember 1966 as a small turbofan for "half-size" business jets, the BS.358 is of modular construction comprising five sections. After- burning is proposed for military applications. Initial component development is under way. Application Domier universal trainer project, 2xBS.358-l (2,0001b) basic, 3,7501b with afterburning. (BS.358-1) Front-fan twin-spool layout, straight-through flow annular combustor, and concentric primary and secondary exhausts. Take-off 2,0001b basic, 3,7501b with afterburning. Length (without afterburner) 40in; diameter 19in; weight 3461b. BS.347 Civil and military single-shaft turbojet. Announced in April 1966 as a new design of ultra-small expendable turbojet for target and reconnaissance drones or as a booster unit for sailplanes, the BS.347 was originally proposed for the Canadair CL-89 reconnais- sance drone. No subsequent applications have been announced. (BS.347/2) Single-stage centrifugal compressor, annular combustor, single-stage axial turbine. Maximum rating 1401b; s.f.c. 1.21b/lb/hr; length 20in; diameter 11.85in; weight 301b. M45H Civil twin-spool turbofan. BED is project leader of M45H designed to power the VFW 614 and being jointly developed by BED and Snecma as latest member of M45 family of engines. West German government has cleared payment of DM50 million to BED, representing 50 per cent of development costs, remaining funding being provided by the two engine companies. First run of M45H is scheduled for mid-1968 with type-approval following about two and a half years later. (M45H) Single-stage l.p. fan plus five-stage i.p. compressor (both driven by l.p. turbine), seven-stage hp compressor, annular com- bustor, single-stage hp turbine, three-stage l.p. turbine. Take-off 7,7601b; b.p.r. 3:1; mass flow 2301b/sec; pressure ratio 18:1 overall: length 116.0in; width 42.9in; weight 1,4831b. Olympus 593 Civil twin-spool augmented turbojet. Power unit for the Mach 2.2 Concorde being jointly developed on a 60/40 basis by BED and Snecma, the Olympus 593 is derived from the Olympus 593D itself a civil counterpart of the Olympus 320 developed for the BAC TSR-2. BED is responsible for the engine as a gas generator, and Snecma has authority for the entire exhaust system. Development is well advanced with 19 engines built, and 2,250hr testing, including 52hr in the Vulcan test bed so far completed. Development potential to about 40,0001b. (Olympus 593) Seven-stage l.p. compressor, seven-stage h.p. com- pressor, cannular combustor with eight flame tubes, single-stage h.p. and l.p. turbines, simple single-gutter afterburner, cascade-type thrust reverser, multi-lobe retractable noise suppressor, multi-flap independently variable primary and secondary nozzles. Take-off 32,8001b basic and 35,0801b with afterburning (de-rated Stage 1 on entry into service in 1971), and 35,0801b basic (full rating Stage 2 after two years in service, in 1973). Mass flow 4501b/sec; pressure ratio 15:1; length (flange-to-flange) 138.22in; (intake-to-exhaust nozzle) approx 280in; inlet diameter 47.85in; weight approx 5,6001b. Pegasus Military vectored-thrust twin-spool turbofan. Pioneer vectored-thrust engine, Pegasus is in advanced stage of military certification for production deliveries for RAF Harriers this year. Initial development to higher ratings is under way, funded by MinTech. Thrust potential is about 24,0001b. Over 10,000 V/STOL sorties have been flown by Pegasus-powered aircraft. Applications Dornier Do31, 2 X Pegasus BPg5 (15,5001b), Rolls- Royce Flying Pig 4xPegasus (24,0001b). Hawker Siddeley P1127, IX Pegasus. Hawker Siddeley Kestrel FGA Mkl/XV-6A, lx Pegasus BPg5 (15,2001b). Hawker Siddeley Harrier, lx Pegasus BPg6 MklOl (19,0001b). (Pegasus BPg6 MklOl) Three-stage l.p. fan, eight-stage h.p. com- pressor, annular combustor, two-stage h.p. & l.p. turbines, separate thrust-vectoring nozzles for fan and turbine flows. Take-off 19,0001b; length 98.9in ; diameter 48in ; weight approx 2,8201b. Viper Civil and military single-shaft turbojet. Well over 2,000 Viper engines have been built and one million hours flown in service with 14 air forces and numerous executive operators. Latest version is Viper 600 of 3,7501b for second-generation business jets. Manu- facture is licensed to Piaggio, Yugoslav Government, Hindustan Aeronautics and the Commonwealth Aircraft Corporation. Applications Aermacchi MB326 A, B, D, F, & H, lx Viper II Mk22/1 (2,5001b); MB326G, IXViper 20F-20 Mk540 (3,4101b). Atlas Aircraft Impala, lx Viper. BAC Jet Provost T3, lx Viper 8 MklO2 (1,7501b); Jet Provost T4 & T5/BAC145, lx Viper 11 Mk 202 (2,5001b); BAC167, lx Viper 20F-20 Mk535 (3,4101b). GAF Jindivik Mkl03A, IX Viper 11 Mk201 (2,5001b). Hawker Siddeley HS125 Series 1, 2xViper 520 (3,0001b); HS125 Series 1A & IB, 2 X Viper 521 (3,1301b) or Viper 522 (3,3601b); HS125 Series 3A, 3AR & 3B. 2 X Viper 522 (3,3601b). Hawker Siddeley Shackleton MR Mk3 Phase 3, 2 X Viper 11 Mk203 (2,7001b). Hindustan HJT-16 Kiran, lx Viper 11 Mk22/8 (2,5001b). Piaggio PD808, 2 X Viper 526 (3,3601b). SOKO G2-A Galeb, lx Viper 11 Mk22/6 (2,5001b). SOKO Jastreb, IX Viper Mk531 (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 85.0in; diameter 24.5in.
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