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Aviation History
1966
1966 - 0032.PDF
26 FLIGHT International, 6 January I9t>i Ttirbomtu Aubisque geared twin-spool turbofan. Single-stage axial fan driven by main rotor via reduction searing. Sinfle-stage axial plus single-stage centrifugal compre«or, with single-iided impeller, of 4?.0lb/sec mass flow and 6.9 : I pressure ratio. Annular reverse-flow combustion chamber. Two-stage axial turbine. Rating, 1,5431b. Weight, 6401b. Diameter, 25.6in (Mock-upshown) Turbomeca Turmo HID free-turbine turboprop. Single-stage axial plus single-stage centrifugal compressor with single-sided impeller of I3.4lb/sec mass flow and 5.8 : I pressure ratio. Annular reverse-flow combustion system. Two-stags axial compressor- turbine, two-stage axial free-turbine. Rating, l,028e.h.p. Weight, 6941b. Width, 37.0in Turbomeca Astazou XII single-shaft turboprop. Two-stage axial plus single-stage centrifugal compressor, with single-sided impeller, of 7.8 : I pressure ratio. Annular reverse-flow combustion chamber. Three-stage axial turbine. Rating, 670c.h.p. Weight 2811b. Diameter, 18.1 in AERO ENGINES . . . between Turbomeca and Augusta in Italy provides for joint manufacture of the TM-251 turboshaft. These companies, together with Turbo- meca, have manufactured a total of some 12,000 engines to Turbomeca designs. Major Turbomeca engines at present in- clude Marbore' VI turbojet, Aubisque turbofan and the Tunno, Bastan, Artouste and Astazcu turboprops and turboshafts. Derived from one of the earliest Turbomeca designs, the Marbor6 VI is rated at 1,0581b and powers such aircraft as the Morane- Saulnier Paris, Potez 94 and CM173 and the Spanish Hispano HA-200 Saeta. More Marbore' turbo jets have been built than any other Turborheca engine. The Aubisque turbofan is in production for the Saab-105 twin-engine multi-purpose aircraft at a rating of l,543ib thrust. A run of 300 Aubisques is being built against contracts for 130 aircraft. The Turmo turboshaft powering the Sud-Aviation Frelon and Super Frelon helicopters has been progressively de- veloped from the Turmo HIC of 1,184 s.h.p., through the Tunno IIIQ of 1,282 s.h.p. to the Tunno IIIQ of 1,480 sJi.p. The Turmo IIID3 turboprop of 1,430 e.s.h.p. powers the four-engine Breguet 941. Of second-generation design, the Bastan VIC turboprop, rated at 1,065 e.s.h.p. has two axial stages ahead of the single-stage centrifugal compressor. These provide an increased pressure ratio which contributes to the low s.f.c. of 0-5781b/e.s.h.p./hr. The Bastan VIC powers the Nord 262 and the Argentinian Dinfia Guarani II. Also derived from an early Turbomeca design, the Artouste has been built in con- siderable quantities for the Sud-Aviation Alouette helicopter. The Artouste IIC5 and C6, both of 523 s.h.p., power the Alouette II. The Artouste IIIB, rated at 550 s.h.p., with a three-stage compressor similar to that on the Bastan, powers the Alouette III. The Astazou has evolved through several phases which have raised the take-off rat- ing of the Astazou II of 555 e.s.h.p. to 740 c.i.h.p. for the Astazou XII. In turbo- prop form and incorporating a single axial stage ahead of the single-stage centrifugal compressor, the Astazou II powers the Pilatus Turbo-Porter and the Sud-Aviation Marquis. The same engine as a turbo- shaft is fitted in the Sud-Aviation Alouette- Astazou helicopter. The more powerful Astazou X and XII turboprops with an additional axial stage have been selected for the Potez 842 and Short Skyvan. An Astazou XIV of 850 e.s.h.p. is planned for delivery in 1967. The Oredon III is a close derivative of the Astazou and has a three-stage com- pressor giving the remarkably high pres- sure ratio of 7.5:1. The engine, which is intended to power future light helicopters, is rated at 350 s.h.p. In the joint Turbo- meca/Bristol Siddeley development pro- gramme the British company is primarily responsible for the main reduction gearbox. A similar arrangement applies to the TM-251 turboshaft whereby Turbomeca provides the power unit (essentially an Astazou with single-stage centrifugal com- pressor) and Agusta supplies the reduc- tion gearbox. Designated TAA230 by Agusta, the engine is rated at 310 sii.p. and powers the Agusta A.105 light heli- copter. GERMANY MAN-TURBO Munich. ~" Formed in mid-1965 as a merger of the former MAN-Turbomotoren GmbH and BMW Triebwerkbau GmbH, this company is largest aero-engine enterprise in Ger- many. From its MAN predecessor, MAN- Turbo inherited licence manufacture of the Tyne turboprop for the European consor- tium and a valuable background of tech- nical collaboration with Rolls-Royce on the RB.153 and 193 turbofans and the RB.145 turbojet. Accompanying this, at Munich, was the most comprehensive aero-engine development organisation in Germany to- day. From the company's BMW predeces- sor came licensed manufacture work on the General Electric J79-GE-11A turbojet for European F-lOAGs, and a series of small turbines of BMW design. Three current engines in the BMW series are the 6012 and 6022 turboshafts and the 8026 turbojet. The 6012, with ratings rang- ing from 60 s.h.p. to 100 s.h.p., has as its Rolls-Royca/MAN-Turbo RB.I93 twin-spool vectored-thrust turbofan. No design details ravaalad. Rating. 10,0001b to I2,000lb. (Picture shows model)
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