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Aviation History
1970
1970 - 0042.PDF
FLIGHT International. I January 1970 26 AERO ENGINES 1970 . . . engines, RB.162 has been readily adapted to booster role. Its sole application to date is in the Hawker Siddeley Trident 3B (1X RB. 162-86) where the booster engine is mounted above the centre Spey main turbofan. Booster improves short-field and engine-out performance, gives rapid climb out and reduces fly-over noise. First RB.162-86 planned to be delivered to Hawker Siddeley in June 1970. (RB.162-86) Configuration same as RB.162 liftjet. Take-off 5,4001b; length 54in; diameter 29in; weight 6001b. RB.10S Military single-shaft liftjet. Pioneer liftjet powering experi mental V/STOL aircraft and hover rigs. Applications Dassault Balzac, 8XRB.108. Dornier Hover Rig, 4XRB.108. EWR-Sud Hover Rig, 3XRB.108. EWR Wippe Rig, 1XRB.108. Fiat Hover Rig, 2XRB.108. Short SCI, 5XRB.108. VFW SG-1262 Hover Rig, 5XRB.108. (RB.108) Eight-stage compressor, annular combustor, single-stage turbine. Take-off 2,2101b (total, with 11 per cent air bleed); mass flow 38.851b/sec; pressure ratio 5.33:1: length 48.3in; diameter 20.8in; weight 2691b. Tyne Civil and military two-shaft turboprop. Sole example of a two-shaft turboprop to enter service, the Tyne for its French and German application is licerice-manufactured by the European Con sortium comprising Snecma, Motoren und Turbinen Union, Fab- rique Nationale and Rolls-Royce. Applications Aviation Traders Merchantman (Vanguard conver sion), 4 X Tyne RTy.l Mk 506 (4,785 e.h.p.) or Tyne RTy.ll Mk 512 (5,325 e.h.p.). BAC Vanguard 951, 4xTyne RTy.l Mk 506 (4,785 e.h.p.). BAC Vanguard 952, 4xTyne RTy.ll Mk 512 (5,325 e.h.p.). Breguet 1150 Atlantic, 2xTyne RTy.20 Mk 21 (6,105 e.h.p.). Canadair CL-44D-4, 4xTyne RTy.12 Mk 515 (5,500 e.h.p.). Canad- air CL-44J & CC-106 Yukon, 4xTyne RTy.12 Mk 515/10 (5,730 e.h.p. Conroy CL-44-O, 4 X Tyne RTy.12 Mk 575 (5,500 e.h.p.). Fairchild C-119 Boxcar project, 2xTyne. Short Belfast C.l, 4 x Tyne RTy.12 Mk 101 (5,715 e.h.p.). Transall C,160D, 2 x Tyne RTy.20 Mk 22 (6,100 e.h.p.). (Tyne RTy.20) Six-tage 1-p compressor, nine-stage h-p compres sor, cannular combustor with ten flame tubes, single-stage h-p tur bine, three-stage 1-p turbine. Integral, front-mounted gearbox. Take off 5,855 e.h.p.; mass flow 46.51b/sec; pressure ratio 13.5:1; length 108.7in; diameter 43.2in; weight 2,2181b. Dart Civil and military single-shaft turboprop. Outstandingly successful 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, 4 X Dart RDa.6 Mk 510 (1,670 e.h.p.). BAC Viscount 800,4 X Dart 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\ lxDart RDa.7 Mk 21 (2,020 e.h.p.). Cavalier Aircraft Mustang 3 Conversion, lxDart RDa.6 Mk 510 (1,440 s.h.p.) or Dart RDa.7/2 Mk 529 (2,185 s.h.p.). Conroy/Douglas Turbo Three, 2xDart Mk 510 (1,670 e.h.p.). Con- roy/Grumman Albatross conversion, 2 X Dart. Convair 600/640, 2x Dart RDa.10 Mk 542-4 (3,025 e.p.h.). Fairchild Hiller F-27, 2x Dart RDa.6 Mk 511 (1,670 e.h.p.). Fairchild Hiller F-27A & F, 2xDart RDa.7 Mk 528-7E (2,105 e.h-p.). Fairchild Hiller F-27B, 2XDart 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, 2xDart RDa.6 Mk 517-7 (1,850 eJi.p.). Fokker F.27 Series 200, 400 & 500, 2 X Dart 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, 2XDart RDa.7/2 Mk 526 (2,020 e.h.p.). Handley Page Herald Series 200 and 400, 2 XDart RDa.7/2 Mk 527 (2,105 e.h.p.). Hawker Siddeley Argosy 220, 4X 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, 2 X Dart RDa.7/2 Mk 530 or 531 (2,020 e.h.p.). Hawker Siddeley Andover C.l, 2XDart RDa.12 Mk 201 (3,245 e.h.p.). Hawker Siddeley Andover CC.2, 2 x Dart R.Da.7 Mk 532 (2,230 e.h.p.). NAMC YS-11 and YS-11A, 2 x Dart 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. Gazelle Military free-turbine turboshaft. Originally of Napier design, has prime application in the Westland Wessex helicopter. Applications Westland Belvedere HC.l, 2 X Gazelle NGa2 Mk 101 1,610 s.h.p.). Westland Wessex HAS.l, lxGazeUe NGal3 Mk 161 (1,410 s.h.p.). Westland Wessex HAS.3, lx Gazelle NGa22 Mk 165 (1,600 s.h.p.). Westland Wessex HAS.31, lx Gazelle NGa. 13/2 Mk 162 (1,540 s.h.p.). Westland Wessex Mk 31b, lxGazelle NGa22 Mk 165C (1,600 s.h.p.). (Gazelle NGa22 Mk 165) Eleven-stage compressor, tubular com bustor with six flame tubes, two-stage compressor-turbine, single- stage power turbine. Integral rear-mounted gearbox. Take-off 1,600 s.h.p.: mass flow 17.61b/sec; pressure ratio 6.35:1; length 75in; diameter 33.5in; weight 8701b. Bristol Engine Division. Headquarters: Bristol, England RB.199 Military three-shaft augmented turbofan. The Division has design and development leadership for the RB.199, under the aegis of Turbo-Union Ltd (q.v.), as powerplant for the Panavia MRCA-75. M45H Civil two-shaft turbofan. The Division is project leader of the 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 in January 1969 at Bristol, and first flight of 614 late this 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. Type approval is planned for January 1972. Applications Sud-Aviation Rotojet Project, 3XM45H. VFW 614, 2XM45H (7,7001b). Westland WG.22 project, 2xM45. (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 7,760lb; b.p.r. 2.85:1; mass flow 2331b/ sec; pressure ratio 18.8:1; length 116.0in; diameter 42.9in; weight 1,4831b. Pegasus Military two-shaft vectored*thrust turbofan. Pioneer vectored-thrust engine. Pegasus 6 Mk 101 of 19,2001b received type approval in March 1968 and entered service in April 1969 powering RAF Harriers. Fan fires, now rectified, caused six weeks ground ing during October/November 1969. Higher-rated Pegasus 10 tested during 1968 with 21,5001b Pegasus 11 for Harrier Mks 50 and 51 scheduled to run in latter part of 1969 with type-approval, as Mk 803, in 1971. Features redesigned fan and higher turbine tempera ture. Mk 101 engines can be modified to Mk 803 standard. Further growth to at least 25,0001b proposed via increased fan mass/flow and turbine temperature plus improved component efficiency giving Pegasus 12, 12D and 13 and, with 2in increased fan diameter, Pegasus 9, 14 and 15. Applications Dornier Do31, 2 X Pegasus 5-2 (15,5001b). Rolls-Royce Flying Pig, 4xPegasus (24,0001b). Hawker Siddeley P. 1127, lx Pegasus 3 (14,0001b). Hawker Siddeley Kestrel FGA.1/XV-6A, lxPegasus 5 (15,2001b). Hawker Siddeley Harrier GR.l and T.2, IX Pegasus 6 Mk 101 (19,5001b). (Pegasus 6 Mk 101) Three-stage 1-p fan, eight-stage h-p compres sor, 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. Olympus 593 Civil two-shaft augmented turbojet. Power unit for the Mach 2.2 Concorde being jointly developed by the Division and Snecma, the Olympus 593 being derived from the Olympus 593D, itself a civil counterpart of the Olympus 320 for the erst while BAC TSR-2. R-R is responsible for the engine as a gas generator and Snecma has authority for the entire exhaust system. Programme is shared approximately 50/50, and development is well advanced with over 30 593s built. Following the first flight in Con corde in March 1969, operation of the engines in 001 and 002 was reported as exceptionally good. Over 8,500hr total test time has now been completed, 75 per cent of this being on the bench. Con corde 001, with its 32,9001b Olympus 593-2As cleared to Mach 1.6, exceeded 1,000 m.p.h. last month. Flight clearance of 34.7001b Olympus 593-3Bs to Mach 2 as imminent. The Stage O engine of 38,0501b, now designated Mk 601, is to be available for service in 1973. After two year's airline service it becomes Mk 611 (pre viously Stage 1) and without further modification is re-rated to 38,4001b. A subsequent new version with annular combustor and other changes giving reduced s.f.c. and lower weight is Mk 621 also of 38,4001b. Kits to be available for converting Mk 611 to Mk 621. Engine has growth potential to around 40,0001b. (See also Concorde Engine Support Organisation Ltd.) (Olympus 593 Mk 601) Seven-stage 1-p compressor, seven-stage h-p compressor, 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 38,0501b; mass flow 4501b/sec; pressure ratio 9.3:1; length (flange to flange) 138.22in; length (intake flange to final nozzle) 280in; diameter 47.85in; weight 5,8141b. Olympus Military two-shaft turbojet. Sole application is Hawker Siddeley Vulcan. Provided basis for Concorde engine. Applications Hawker Siddeley Vulcan B.l, 4x Olympus Mk 101 (11,0001b) or Mk 102 (12,0001b) or Mk 104 (13,5001b). Hawker Siddeley Vulcan B.2, 4 X Olympus Mk 201 (17,O01b) or Mk 301 (20,0001b).
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