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Aviation History
1968
1968 - 0025.PDF
FLIGHT International, 4 January 1968 27 Representing the new family of triple-shaft engines, the Rolls-Royce Trent will power the Fairchild Hitler FH-228 civil transport RB.168-25R Spey Military twin-spool augmented turbofan. Under development as Britain's first supersonic afterburning turbofan, powers RN and RAF McDonnell F-4K and F-4M Phantoms. Based on military subsonic RB. 168-20. Applications McDonnell F-4K & F-4M Phantoms, 2XRB.168-25R Mk 201 (12,5001b or 21,2501b with afterburner). RB.168-25R Mk 201 Configuration similar to Spey-25. Fully thrust modulating afterburner with variable convergent nozzle and fixed divergent ejector nozzle. Take-off 12,5001b basic or 21,2501b with afterburning. RB.168-20 Spey Military twin-spool turbofan. Closely based on the civil Spey-25 Mk 511, is under development to power maritime reconnaissance derivative of the Comet. Has modified accessory gearbox to drive extra large alternator, and features extensive anti-corrosive treatment. Application Hawker Siddeley HS.801 Nimrod, 4 X RB.168-20 Mk 250. (RB.168-20 Mk 250) Configuration similar to Spey-25 Mk 511. RB.168-1 Spey Military twin-spool turbofan. Initial military version of civil Spey. Is counterpart to the commercial RB. 163-1 and has application only in the Hawker Siddeley Buccaneer SI and S.50. (RB.168-1 Mk 101) Configuration similar to Spey-1. RB.163-25 Spey Civil twin-spool turbofan. Latest version of com- mercial Spey, developed primarily to power larger versions of the Hawker Siddeley Trident and BAC One-Eleven. Applications BAC One-Eleven Series 300/400, 2 X RB.163-25 Mk 511-14 (11,4001b). BAC One-Eleven Series 300/400 & 500, 2 x RB.163-25 Mk 512-14 (12,0001b). Grumman Gulfstream II, 2XRB.163-25 Mk 511-18 (11,4001b). Hawker Siddeley, Trident IE, 3XRB.163-25 Mk 511-5 (11,4001b). Hawker Siddeley Trident 2E & 3B, 3 X RB.163-25 Mk 512-5 (11,9601b). (RB.163-2 Mk 506-14) Four-stage fan/l.p. compressor, 12-stage h.p. compressor, cannular combustor with ten flame tubes, two- stage h.p. and l.p. turbines. Take-off 12,0001b to 90°F; b.p.r. 0.7:1; mass flow 2071b/sec; pressure ratio 207.1; length 125in; width 41in; height 45in; weight 2,5901b. RB.163-2 Spey Civil twin-spool turbofan. Intermediate version of the Spey introduced to power the BAC One-Eleven Series 200. (RB.163-2 Mk 506-14) Four-stage fan/l.p. compressor, 12-stage h.p. compressor, cannular combustor with ten flame tubes, two- stage h.p. and l.p. turbines. Take-off 10,4101b; b.p.r. 1.0:1; mass flow 208 lb/sec; pressure ratio 16.9:1; length HOin; width 41in; height 45iri; weight 2,3061b. RB.163-1 Spey Civil twin-spool turbofan. Initial version of civil Spey launched to power the Hawker Siddeley Trident 1 and 1C. (RB.163-1 Mk 505-5) Four-stage fan/l.p. compressor, 12-stage h.p. compressor, cannular combustor with ten flame tubes, two-stage h.p. and l.p. turbines. Take-off 9,8501b; b.p.r. 1.0:1; mass flow 2O31b/sec; pressure ratio 16.8:1; length llOin; width 41in; height 45in; weight 2,2201b. RB.162 Military single-shaft lift engine. Second-generation Rolls- Royce lift engine powering experimental V/STOL aircraft. Develop- ment is financed by the British, German and French governments, and Rolls-Royce. Applications Dassault Mirage IIIV, 8 XRB.162-31 (5,6001b). Dornier Do31E, 8XRB.162-4D (4,4001b). VFW VAK/191B, 2XRB.162-81 (6,0001b). (RB162-81) Six-stage compressor, annular combustor, single-stage turbine. Take-off 6,0001b (with 10 per cent air bleed); pressure ratio 4.25:1; length 50in; diameter 29in; weight 3751b. Tyne Civil and military twin-spool turboprop. Sole example of a twin-spool turboprop to enter service, the Tyne for its French and German application is license-manufactured by the European Con- sortium comprising Hispano-Suiza, MAN Turbo and Fabrique Nationale. Applications BAC Vanguard 951, 4 x Tyne R Tyl Mk 506 (4,785 e.h.p.). BAC Vanguard 952, 4xTyne R Tyll Mk 512 (5,325 e.h.p.). Breguet 1150 Atlantic, 2 X Tyne R Ty20 Mk 21 (6,105 e.h.p.). Canadair CL-44D-4, 4X Tyne R Tyl2 Mk 515 (5,500 e.h.p.). Canadair CL-44J & CC-106 Yukon, 4xTyne R Tyl2 Mk 515/10 (5,730 e.h.p.). Short Belfast C Mk 1, 4xTyne R Tyl2 Mk 101 (5,715 e.h.p.). Transall C-160D, 2xTyne R Ty20 Mk 22 (6,100 e.h.p.). (Tyne R Ty20) Six-stage l.p. compressor, nine-stage h.p. com- pressor, cannular combustor with ten flame tubes, single-stage h.p. turbine, three-stage l.p. turbine. Integral, front-mounted gear- box. 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. RB.108 Military single-shaft lift engine. Pioneer lift engine power- ing experimental V/STOL aircraft and hover rigs. Applications Dassault Balzac, 8 X RB.108. Dornier Hover Rig, 4 X RB.108. EWR-Sud Hover Rig, 3 x RB.108. EWR Wippe Rig, lxRB.108. Fiat Hover Rig 2XRB.108. Short SC.l, 5XRB.108. VFW Hover Rig, 5 X RB.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. 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 (1,465 s.h.p.). Westland Wessex HAS Mk 1, lx Gazelle NGal3 Mk 161 (1,450 s.h.p.). Westland Wessex HAS Mk 3, IX Gazelle NGa22 Mk 165 (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. Conway RC.42 and 43 Civil and military twin-spool turbofan. Final variants of the Conway, developed specifically to power the BAC VC10 and Super VC10. Applications BAC VC10, 4 X Conway RCo.42 Mk 540 (20,3701b). BAC VC10 C Mk 1, 4 X Conway RCo.43 Mk 301 (22,5001b). BAC Super VC10, 4 X Conway RCo.43 Mk 550 (21,8001b). (Conway RCo.43 Mk 550) Four-stage fan/l.p. compressor plus four-stage i.p. compressor, nine-stage h.p. compressor, cannular combustor with ten flame tubes, single-stage h.p. turbine, two-stage l.p. turbine. Take-off 21,8001b; b.p.r. 0.6:1; mass flow 3751b/sec; pressure ratio 15.8:1; length 154in; diameter 50in; weight 5,1011b. Conway R.Co.17 Military twin-spool turbofan. Sole application is the Handley Page Victor B2 as the 20,6001b Mk 201. Conway R.Co.12 Civil twin-spool turbofan. Pioneering commercial turbofan derived from the original military engine for the Vickers V.1000. Applications Boeing 707-420, 4 X Conway RCo.12 Mk 508 (17,5001b). Douglas DC-8 Series 40, 4 x Conway R.Co.12 Mk 509 (17,5001b). (Conway R.Co.12 Mk 509) Seven-stage fan/l.p. compressor, nine- stage h.p. compressor, cannular combustor with ten flame tubes, single-stage h.p. turbine, two-stage l.p. turbine. Take-off 17,0001b; b.p.r. 0.3:1; mass flow 2801b/sec; pressure ratio 14:1; length 136in; diameter 42in; weight 4,5421b. RB.146 Avon 300 Military single-shaft augmented turbojet. Most powerful military Avon, introduced for later versions of the BAC Lightning. License manufactured by Flygmotor as RM6, with Swedish afterburner, for Saab 35 Draken. Applications BAC Lightning F6 and T5, 2 X Avon Mk 301 (12,6901b, or 16,3601b with afterburning). Avon RA.29 Civil and military single-shaft turbojet. Derived from the Avon 200 series for commercial operation. Applications Hawker Siddeley Comet 4 & 4C, 4 X Avon RA.29/I Mk 524B (10,2501b). Hawker Siddeley Comet 4B, 4 x Avon RA.29/I Mk 525B (10,2501b). Sud-Aviation Caravelle III, 2xAvon RA.29/3 Mk 527B (11,4001b). Sud-Aviation Caravelle VI N, 2 X Avon RA.29/3 Mk 531B (12,2001b). Sud-Aviation Caravelle VI R, 2 X Avon RA.29/3 Mk 533R (12,6001b). (Avon RA.29/I) Sixteen-stage compressor, cannular combustor, three-stage turbine. Take-off 10,2501b; pressure ratio 9.08:1; length 126in; diameter 39in; weight 3,3431b.
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