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Aviation History
1969
1969 - 0040.PDF
Power unit for Concorde, the Olympus 593 augmented turbojet is being developed jointly by the Bristol Engine Division of Rolls-Royce and Snecma. The Olympus 593 may eventually develop a total thrust of40,000lb AERO ENGINES 1969 . . . - F-227B, 2XDart RDa.7 Mk 532-7 (2.250 e.h.D.). Fokker F.27 Series 100 & 300, 2XDart RDa.6 Mk 517-7 (1,850 e.h.p.). Fokker F27 Series 200, 400 & 500, 2 XDart RDa.7 Mk 532-7 (2,255 e.h.p.). Grumman Gulfstream I, 2 X Dart RDa.7/2 Mk 529-8 and E (2,100 e.h.p.). Handley Page Herald Series 100, 2 X Dart RDa.7/2 Mk 526 (2.020 e.h.p,). Handley Page Herald Series 200 and 400, 2X Dart RDa.7/2 Mk 527 (2,105 e.h.D.). Hawker Siddeley Argosy 220. 4xDart 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, 2 X Dart 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. 2XDart RDa.12 Mk 201 (3,245 e.h.p.). Hawker Siddeley Andover CC Mk 2, 2X Dart RDa.7 Mk 532 (2,230 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 27Ib/sec; pressure ratio 6.3:1. length 98in : diameter 38in; weight 1,3371b. Rolls-Royce Bristol Engine Division RB.199 Military three-shaft turbofan. Introducing R-R three- shaft technology to BED, RB.199 is rated around 9,0001b as possible engine for MRCA project. M45H Civil twin-spool turbofan. BED is project leader of M45H designed to meet special low s.f.c. short-haul propulsion requirements of VFW 614. Being jointly developed and manufac tured by R-R and Snecma. German government supplying 50 per cent of development costs with remaining finance being provided by two engine companies. Clearance given for manufacture of total of 21 bench, flight and production standard engines. First run was scheduled for last month at Bristol, and first flight of 614 late next year. Phase 1 M45H-C to give full 8,2451b design rating, with slightly modified Phase 2 engines giving over 9,0001b. Initial Phase 1 engines (M45H-D) being supplied derated to 7,7601b. (M45H-D) Single-stage fan, five-stage i-p compressor, seven- stage h-p compressor, annular combustor, single-stage h-p turbine, three-stage 1-p turbine. Take-off 7,7601b; b.p.r. 2.8.1, mass flow 2331b/sec; pressure ratio 18.8:1: length 116.0in: diameter 42.9in; weight 1,4831b. Olympus 593 Civil twin-spool augmented turbojet. Power unit for the Mach 2.2 Concorde being jointly developed 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 31 engines built, and close on 5,000hr testing, including over HOhr in the Vulcan test bed so far completed. Later production engines likely to have advanced plug nozzle type noise suppressor to further reduce airfield noise. Development potential to about 40,0001b. (Olympus 593) Seven-stage 1-p compressor, seven-stage h-p com pressor, cannular combustor with eight flame tubes, single-stage h-p and 1-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 28 FLIGHT International, 2 January 1969 32,8251b 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 9.3:1; length (flange-to-flange) 148.4in; (intake-to-exhaust nozzle) approx 280in; inlet diameter ,47.85in; weight 5,8141b. Pegasus Military vectored-thrust twin-spool turbofan. Pioneer vectored-thrust engine. Pegasus received type approval last year and production deliveries now being made for RAF Harriers. Initial development to higher ratings is under way as Pegasus BPgll, funded by MinTech. First run of this uprated version of BPg6 late 1968 for service availability in early 1970s. Thrust potential is about 24,0001b. Over 10,000 V/STOL sorties have been flown by Pegasus-powered aircraft. Applications Dornier Do31, 2xPegasus BPg5 (15,5001b). Rolls- Royce Flying Pig 4 x Pegasus (24,0001b). Hawker Siddeley PI 127, IX Pegasus 3 (14,0001b). Hawker Siddeley Kestrel FGA Mk 1/ XV-6A, lx Pegasus BPg5 (15,2001b). Hawker Siddeley Harrier GR1 and T2, 1 X Pegasus BPg6 Mk 101 (19,5001b). (Pegasus BPg6 Mk 101) Three-stage 1-p fan, eight-stage h-p com pressor, annular combustor, two-stage h-p & 1-p turbines, separate thrust-vectoring nozzles for fan and turbine flows. Take-off 19,5001b with water injection: length 98.9in; diameter 48in; weight approx 2,8201b. Viper Civil and military single-shaft turbojet. Over 3,000 Viper engines have been built and one and one-quarter million hours flown in-service with 19 air forces and numerous executive operators. Latest version is Viper 600 of 3,7501b for second- generation business jets and COIN/trainer aircraft. Manufacture is licensed to Piaggio, Yugoslav Government, Hindustan Aero nautics, Atlas Aircraft Corporation and the Commonwealth Air craft Corporation. Engine has 20 applications. Applications Aermacchi MB326 A, B, D, F, & H, lxViper 11 Mk 22/1 (2,5001b); MB326G & K, IX Viper 20F-20 Mk 540 (3,3601b). Atlas Aircraft Imnala. lXVioer. BAC Jet Provost T3, IX Viper 8 Mk 102 (1,7501b); Jet *Provost T4 & T5/BAC145, lXViDer 11 Mk 202 (2,5001b); BAC167, IX Viper 20F-20 Mk 535 (3,3601b). GAF Jindivik Mk 103A, lxViner 11 Mk 201 (2,5001b). Hawker Siddeley HS125 Series 1, 2xViper 520 (3,0001b): HS125 Series 1A & IB, 2X Viper 521 (3,130lb) or Viper 522 (3,3601b): HS125 Series 2/Dominie T Mk 1, 2XHS125 Series 3A, 3AR & 3B, 2 X Viper 522 (3,3601b). Hawker Siddeley Shackleton MR Mk 3 Phase 3, 2x Viper 11 Mk 203 (2,7001b). Hindustan HJT-16 Khan, lx Viper 11 Mk 22/8 (2,5001b). Piaggio PD808, 2 X Viper 526 (3,3601b). SOKO G2-A Galeb, lx Viper 11 Mk 22/6 (2,5001b). SOKO Jastreb, IX Viper 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 71.1in; diameter 24.5in; weight 7751b. 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, IX Orpheus 80302 (5,0001b): Fiat G.91R/3 & G.91T/3, lxOrpheus 803D Hll (5.0001b). Fuji T1F-2. lxOroheus 805 (4,0001b). Hawker Siddeley Gnat Mk 1. IXOrpheus 701 (4,7001b): Hawker Siddeley Gnat Tl, lxOrpheus 101 (4,5201b). (Orpheus 803) Seven-stage compressor, cannular combustor with seven flame tubes, single-stage turbine. Take-off 5.0001b; mass flow 84lb/sec; pressure ratio 4.14:1: length 96.1in: diameter 32.4in: weight 9001b. Olympus Military twin-SDOol turbojet. Sole application is Hawker Siddeley Vulcan. Provided basis for Concorde engine. Applications Hawker Siddeley Vulcan B Mk 1. 4xO!ymDUs Mk 101 (11,0001b) or Mk 102 (12,0001b) or Mk 104 (13,5001b). Hawker Siddeley Vulcan B Mk 2 ; 4x01ymDUs Mk 201 (17,0001b) or Mk 301 (20,0001b). (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: legth 131in: diameter 44.5in: weight 4,2901b. Rolls-Royce Small Engine Division BS.360 Military twin-spool free-turbine turboshaft. Planned to run early this year, BS.360 is to be 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 twin-spool free-turbine layout to provide high pressure ratio, low s.f.c. turboshaft easy to maintain in the field. Will be first SED-designed engine to be built since Gyron Junior Is. Designated RS.360 for later applications. (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 ?2imin) 900 s.h.p.; max. power
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