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Aviation History
1970
1970 - 0041.PDF
FLIGHT International, I January 1970 25 drive extra large alternator, and features extensive anti-corrosive treatment. Initial deliveries of Nimrod made in October 1969. Application Hawker Siddeley HS.801 Nimrod MR Mk I, 4XRB.168-20 Mk 250 (11,5001b). (RB.168-20 Mk 250) Configuration similar to Spey-25 Mk 511. ' Take-off 11,5001b. , RB. 168-1A Spey Military two-shaft turbofan. Initial military ver sion of civil Spey. Is counterpart to the commercial RB.163-1 and has application only in the Hawker Siddeley Buccaneer S2 and S50. (RB.168-1A Mk 101) Configuration similar to Spey-1. Take-off 11,1001b. v RB. 163-25 Spey Civil two-shaft turbofan. Latest version of com- t mercial Spey, developed primarily to power larger versions of the Hawker Siddeley Trident and BAC One-Eleven, Applications BAC One-Eleven Series 300-400, 2XRB.163-25 Mk 511-14 (11,4001b). BAC One-Eleven Series 475 & 500, 2x RB.163-25 Mk 512-14DW (12,5501b). Grumman Gulfstream II and VC-11A, 2XRB.163-25 Mk 511-8 (11,4001b). Hawker Siddeley Trident IE, 3XRB.163-25 Mk 511-5 (11,4001b). Hawker Siddeley k Trident 2E, 3XRB.163-25 Mk 512-5W (11,9601b). Hawker Siddeley Mf Trident 3E, 3XRB.163-25 Mk 512-5W/50 (11,9301b). ™ (RB.163-25 Mk 512-14DW) Five-stage fan/l-p compressor, 12-stage h-p compressor, cannular combustor with ten flame tubes, two-stage h-p and 1-p turbines. Take-off 12,0001b basic rising to 12,5501b with water injection; b.p.r. 0.7:1; mass flow 2061b/sec; pressure ratio 20.7:1; length 125in ; width 41in; height 45in; weight 2,5901b. RB. 163-2 Spey Civil two-shaft turbofan. Intermediate version of i 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 1-p turbines. Take-off 10,4101b; b.p.r. 1.0:1; mass flow 2081b/sec; pressure ratio 16.9:1; length HOin; width 41in : height ' 45in; weight 2,3061b. v RB. 163-1 Spey Civil two-shaft 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 1-p turbines. Take-off 9,8501b; b.p.r. 1.0-1 ; mass flow 2031b/sec: pressure ratio 16.8:1: length HOin; width 41in; height 45in: weight 2,2201b. RB.153 Military two-shaft turbofan. Developed jointly by R-R and Motoren und Turbinen Union (which see for information). Conway RCo.42 and 43 Civil and military two-shaft turbofan. ( Final variants of the Conway, developed specifically to power the BAC VC10 and Super VC10. Selected engines flown in service with carbon fibre fan blading to gain experience for RB.211 programme. ' ", Applications BAC VC10, 4xConway RCo.42 Mk 540 (20,3701b). ' BAC VC10 C Mk 1, 4 X Conway RCo.43 Mk 301 (22,5001b). BAC ' , Super VC10, 4X 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 , 1-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 RCo.17 Military two-shaft turbofan. Sole application is the Handley Page Victor B.2 as the 20,6001b Mk 201. < Conway RCo.12 Civil two-shaft 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, 4X Conway RCo.12 Mk 509 (17,5001b). (Conway RCo.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 1-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 series. *• Applications BAC Lightning F.6, T.5 and T.55, 2 X Avon Mk 301 (12,6901b, or 16,8601b with afterburning). BAC Lightning F.53, 2xAvon Mk 302-C (11,1001b, or 16,3001b with afterburning). Avon RA.29 Civil and military single-shaft turbojet. Derived from T the Avon 200 series for commercial operation. t'« Applications Hawker Siddeley Comet 4 & 4C, 4XAvon RA.29/1 t-? Mk 524B (10,2501b). Hawker Siddeley Comet 4B, 4xAvon RA.29/1 Mk 525B (10,2501b). Sud-Aviation Caravelle III, 2 X Avon RA.29/3 t Mk 527B (11,4001b). Sud-Aviation Caravelle VI N, 2 X Avon RA.29/3 Mk 531B (12,2001b). Sud-Aviation Caravelle VI R, 2x Avon RA.29/3 Mk 533R (12,6001b). (Avon RA.29/1) Sixteen-stage compressor, cannular combustor, , three-stage turbine. Take-off 10,2501b; pressure ratio 9.08:1, length 126in; diameter 39in; weight 3,3431b. Rolls-Royce RB.2I I engine under development for the Lockheed L-I0II TriStar on the open-air test bed. The reverser system can be clearly seen RB.90 Avon 200 Military single-shaft augmented turbojet. Major military version of the Avon. Licence-manufactured by Fabrique Nationale, and by Flygmotor as RM5 with Swedish afterburner to power Saab Lansen. Applications BAC 221, lxAvon RA.28R (14,4301b with after burning). BAC Canberra Mk 9, 2 X Avon RA.24 Mk 206 (11,2501b). BAC Lightning F.2, 3 & 5, 2 X Avon RA.24R Mk 210 (11,2501b, or 14,3701b with afterburning). BAC Scimitar F.l, 2 X Avon RA.24 Mk 202 (11,2501b). Hawker Siddeley Hunter Mks 9, 10 & 12, 1 X Avon RA.28 Mk 207 (10,1501b). Hawker Siddeley Sea Vixen FAW.2, 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. RB.202 Civil two-shaft liftfan. Advanced technology project of novel design believed to include single-stage fan, contra-rotating spools and use of Lungstrom-type radial outflow turbine. Engine length (i.e. height) approximately half fan casing diameter. Proposed for variety of UK and German V/STOL transport projects. Applications Dornier Do231, 12 x RB.202 (13,0501b). Hawker Siddeley and Westland Aircraft V/STOL transport projects, mul tiple RB.202s. VFW VC-180, 10XRB.202-25 (20,5001b). VFW VC- 181, 12XRB.202-25 (14,3501b). (Each aircraft also has two or more cruise-propulsion turbofans.) GRB.162 Civil two-shaft liftfan. Advanced liftfan project probably related to RB.202. Designed to be shallow for installation within depth of wing root, and with high b.p.r. to give low exhaust velocity to reduce noise level. UK industry and Mintech have set tentative target of 90PNdB on ground at 1,500ft below lift-off for total thrust of 80,0001b. (GRB.162) Take-off 8,0001b; b.p.r. 10:1; mass flow (overall) 4001b/sec: length/height 34in; diameter 58.5in. J99 Military two-shaft liftjet. Announced to have run early 1969, the XJ99-RA-1 is the subject of a UK/USA governmental agree ment for joint development of an advanced liftjet for V/STOL applications. Financed on a 50/50 basis, the engine is a collabora tive design by Rolls-Royce and Allison, but reportedly making extensive use of the former's RB.189 third-generation lift-engine technology. Objectives include a thrust/weight ratio of at least 20:1 and a thrust/volume ratio in excess of l,2001b/cu ft, the latter being considerably in advance of present lift-engine attainments. Thrust is understood to be in the region of 9,0001b. Contra-rotation of spools reduces compressor stages required. Liftjet is unique in being only engine to be given a non-American manufacturer's official USAF designation, i.e. RA=Rolls-Royce/Allison. RB.162 Military single-shaft liftjet. Second-generation Rolls-Royce liftjet powering experimental V/STOL aircraft. Development is financed by the British, German and French governments, and Rolls-Royce. A 7,0001b thrust version of the RB.162 proposed for STOL version of Boeing 737 using eight liftjets with swivel exhaust nozzles. Applications Dassault Mirage HI-V, 8XRB.162-31 (5,6001b). Dornier Do31'E, 8XRB.162-4ID (4,4001b). VFW VAK 191B, 2x RB.162-81 (5,5771b). (RB.162-81) 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. RB.162 Civil single-shaft turbojet booster. Through close similarity between operational and design requirements of liftjets and booster
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