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Aviation History
1959
1959 - 0797.PDF
394FLIGHT, 20 March1959 Rolls-Royce Avon RA.29 Mk 527 Commercial single-shaft turbojet. Sixteen-stage compressor, annular combustion chamber with eight flame tubes, three-stage turbine and two-position sound-suppressing nozzle. Installationa) envelope diameter, 39in; diameter outside intake, 35.7in; overall envelope diameter, 43in; length as depicted, room temp., 125.975m, dry weight, 3,327 Ib (including oil and fuel systems, controls and electrics); max sea-level rating, with nozzle in closed position, 11,700 fb at 8,000 r.p.m.; corresponding mass flow and pressure ratio, 173 Ib/sec and 9.63:1; max continuous rating, 9,810 Ib with s.f.c. of 0.749; low-percentage cruise rating at M 0.74 at 35,OOOft, standard day, with nozzle open, 1,820 Ib at 6,850 r.p.m. with s.f.c. of 0.885. Rolls-Royce RB.14S Single-shaft turbojet. Axial compressor with six or seven stages, annular com- bustion chamber and (probably) single-stage tur- bine. Diameter 20.25in; overall length as depicted, 65in; max rating, 2,7501b dry; all other data restricted. Rolls-Royce Conway RCo.10 Mk SOS Commercial by-pass engine. Multi-stage low-pressure (fan) compressor, multi-stage high-pressure compressor, annular combustion chamber with ten flame tubes, independent high- and low-pressure turbines. Diameter across outside of intake, 37.6in; overall installational envelope diameter, under 47.5in; length from nose to turbine exit cone, 134.21 in; max sea-level rated thrust, 17,000 Ib (16,500 guaranteed min.); these engines may be recalibrated to give 500 Ib additional thrust without internal modification. All other data are restricted. (The drawing shows a Boeing Mk 505, complete with reverser and nozzle, but without the U.S.-supplied cabin turbo-compressor.) o O o —T^ e el 1 1 II 1 1" 1 | 1 1 1 1MINI 1 1 1 I 1 1II 1 1 1 1 1 1 1 1 1 1MINI i « m^i Rolls-Royce RB.141 Commercial high-ratio by-pass turbojet. No details have been released, except for the fact that the thrust of the first series will lie between 12,000 and 16,000 Ib, according to application; first deliveries are likely to be rated at 14,300 Ib. The five-foot scale in the drawing is approximate. AERO ENGINES 1959... motors for aircraft. These units are basedupon a regeneratively-cooled chamber rated at Rolls-Royce Dart RDa.7/2 Mk 524-530 Commercial single-shaft turboprop. Two centrifugal compressors in series, seven canted combustion chambers and three-stage turbine. Overall diameter at rear of nose cowl, 33in; max diameter across firewall, 37.9in; length as depicted, 97.64in; dry weight, 1,250 Ib fully equipped; max sea-level rating, usually 1,910 s.h.p. (2,100 e.h.p.) at 15,000 r.p.m. with s.f.c. of 0.66 Ib/hr/ e.h.p.; corresponding mass flow and pressure ratio, 22 Ib/sec and 5.62:1. Dart RDa.10 Similar configuration. Slightly longer; dry weight 1,323 Ib; max sea-level rating 2,440 s.h.p, (2,660 e.h.p.) at 15,000 r.p.m., with s.f.c. of 0.64 Ib/hr/e.h.p. and mass flow and pressure ratio of 25.5 Ib/sec and 6.35:1. 3,000 Ib sea-level thrust, and form an out-standingly compact package complete with turbopump and control system. As the DoubleScorpion, a twin-barrel package has been flight-tested in a Canberra—which gained aworld altitude record while doing so—and a number of these units are in service in Can-berras of the R.A.F. engaged upon special duties. The Double Scorpion is also availableto provide boost propulsion for the Lightning intercepter. Last year details were given ofthe Triple Scorpion, a three-barrel unit scarcely larger than the twin-chamber engine.Each fixed-thrust chamber can be individually fired or shut down. Napier have also taken cold H.T.P. helicop-ter boost systems to an advanced stage of development. Considerable flight experiencehas been gained with equipment mounted on a Skeeter 5 helicopter and a boost system hasalso been designed for the Westiand Whirl- wind. ROLLS-ROYCE Rolls-Royce Ltd.,Derby. During the past three years this renowned company has consolidated its positionas the world's leading producer of gas turbine aero-engines for airline transport operations.At present 54 per cent of the world's turbine airliners (excluding the Communist countries) areequipped or will be equipped with Rolls-Royce powerplants; and this proportion is unlikely tochange substantially during the next five years. The company's operations are sub-dividedamong an aero-engine division, an oil-engine division, a car division, an international divi-sion and Rolls-Royce and Associates Ltd. The last-named is engaged in nuclear power reactorengineering, and Rolls-Royce are also one of the three partners in Vickers NuclearEngineering. The aero-engine division is by far the largest,with some 34,000 employees (of whom about 8,500 are engaged in research and develop-ment). Last September the company's privately financed (£6m) high-altitude test facility forturbo jets and turboprops was formally opened, and in this engines can be tested under con-ditions equivalent to Mach 2.5 and 70,000ft. Derby remains the headquarters of the companyand of the aeroengine division, and the major part of the work upon military and civil aircraftengines, rocket engines and nuclear work is centred in that town. The Scottish group of fac-tories is engaged in the bulk production of mili- tary Avon turbojets, together with spares andoverhauls for the earlier centrifugal turbojets and the support of all piston engines. Otherestablishments are Ilkeston and Mountsorrel, near Derby (jigs, tools and sheet metal), Bar-noldswick, Lanes (research and development) and HucknaO, Notts (flight development estab-lishment). Rolls-Royce also manage the Ministry of Supply rocket test site at Spade-adam, Cumberland. Avon (military) Over 1,750,000 hr has nowbeen logged in squadron service by the thousands of Avon axial turbojets which power Rolls-Royce Tyne RTy.1 Mk 506 Commercial two- spool turboprop. Six-stage low-pressure compressor, nine-stage high-pressure compressor, annular com- bustion chamber with ten flame tubes, single-stage high-pressure turbine and three-stage low-pressure turbine. External diameter over intake, 35.3in; overall installational envelope diameter, 40.5in; length as depicted, room temp., 110.154in; dry weight, 2,220 Ib with all equipment; max sea-level rating. 4,500s.h.p. (4,985 e.h.p.) at 15,250 r.p.m.; correspond- ing mass flow and pressure ratio, 46 Ib/sec and 13:1; typical cruising rating, 425 m.p.h. at 25,000ft, standard day, 2.455 s.h.p. (2,685 e.h.p.) with s.f.c. of 0.405 Ib/hr/ e.h.p. Ratings of later Tynes are given on p. 396.
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