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Aviation History
1974
1974 - 0060.PDF
56 TURBINE ENGINES OF THE WORLD Atar 9K50 Nine-stage compressor, annular combustor, two- stage turbine, afterburner with convergent-divergent nozzle. Take-off 11,0001b basic rising with reheat to 15,4001b; pressure ratio 6-15:1; mass flow 1581b/sec; length 234in; diameter 40-lin; weight 3,4991b. CF6-50 Two-shaft turbofan. Snecma is participating, to the extent of 23 per cent by value, in the production of General Electric CF6-50 turbofans for the Airbus Industrie A300B pro gramme. Other shares are 68 per cent to GE and ten per cent to MTU. Final assembly and test is performed by Snecma. Deliveries started in June last year, and an initial batch of 51 engines are scheduled to have been completed by the end of this year. CFM56 Two-shaft turbofan. This joint venture by Snecma and GE on a fifty-fifty basis is intended to provide a civil turbofan in the 10-12 tonne class, now edging up to 15 tonnes —for availability in the late 1970s. Following announcement of an agreement in November 1971, a joint CFM56 manage ment company (so far un-named) was formed, jointly chaired by the heads of Snecma and GE's Aircraft Engine Group. In the autumn of 1972, US government restrictions on export of the GE F101 military engine technology as the basis of the core for the CFM56, resulted in slowing of the programme. Subsequently in October last year, this embargo was eased with a revised estimate for a later market for the civil engine apparently being a beneficial factor in the decision. Whereas originally Snecma was to be responsible for tech nical direction of the programme, design integration has now become a GE responsibility. Overall programme costs to certification, put at around $400 million, Frl,800 million, are to be shared equally, with each partner taking care of any over-runs on the costs of its portion. Snecma is providing the l-p system and has already completed considerable aero dynamic and acoustic testing of the single-stage fan. GE is providing the h-p system, and with some $300 million, Frl,350 million of US Government funds reportedly already spent on the F101 programme, it seems unlikely that any forthcoming cancellation of its application (the USAF B-l) will unduly jeopardise the CFM56. Each partner may introduce further participating companies within its 50 per cent share, and Snecma has already brought in Fabrique Nationale. First run of the engines is now planned for the middle of this year, at GE Cincinnatti, and certification should be completed by 1977. No firm applications for the CFM56 have so far been established, in particular Snecma has said there is no inten tion to use the engine in derivatives of the Mercure or A300B. With Snecma's participation in the CFM56 being scheduled as part of France's sixth Five-Year Plan, some $20 million, Fr90 million for the engine is understood to be in cluded in the French 1974 civil aviation budget. Laraac Two-shaft turbofan. Snecma and Turbomeca have formed a joint management company, Groupement, Turbo- meca-Snecma GRTS, to handle development of the Larzic turbofan for the Franco-German Alpha Jet trainer (see page 58). M45H Two-shaft turbofan. This engine is a joint project with Rolls-Royce (1971 ) to power the VFW 6J4. R-R is project leader with 60 per cent of development and 65 per cent of production. (For description see page 53.) IVI53 Augmented single-shaft turbofan. Flight testing of the Mach 2-5-3 M53 in the starboard nacelle of a Caravelle started in July last year, and two Mirage F.ls are being modified for supersonic testing of the turbofan later this year. Well over 80hr Hying in the Caravelle has already been completed. Preliminary production of the M53 is already well advanced for the two known applications—the Mirage F.1E International and the ACF (Avion de Combat Futur) project. The first will fly in prototype form late this year, and the Mirage G.8A, predecessor of the ACF, early next year. It is anticipated that the M53 will enter service around 1977. M53 Three-stage fan, five-stage h-p compressor, annular com bustor, two-stage turbine, close-coupled afterburner, ejection- type convergent nozzle. Take-off 12,3501b basic rising with reheat to 18,7001b; bypass ratio 0-4:1; pressure ratio 8-5:1; mass How 185Ib/sec; weight 3,1311b. Olympus 593 Two-shaft turbojet with afterburner. This engine is a joint development by Rolls-Royce (1971 and Snecma to power the Concorde. Snecma, with 40 per cent of the pro gramme, is responsible for the entire exhaust system. See also page 53. FLIGHT International. 10 January 1974 SOLOVIEV (USSR) This design bureau has concentrated very successfully on commercial transport turbofans and large helicopter turbo- shafts. It is also possible, in view of its designation, that the new Lotarev/Ivchenko D-36 turbofan is a Soloviev design. D-20P Two-shaft turbofan. The sole application of this turbo- fan is the twin-engined Tupolev Tu-124. D-20P Three-stage fan, eight-stage h-p compressor, cannular combustor, single-stage h-p turbine, two-stage l-p turbine. Take-off 11,9051b, bypass ratio 1:1; pressure ratio 13:1; mass How 2491b/sec; length 130in; diameter 38-3in; weight 3,2041b: D-25V Free-turbine two-shaft turboshaft. ThTis is the power- unit for the twin-engined Mil Mi-6, the twin-engined Mi-10 and the giant four-engined Mi-12 helicopter. In the last- mentioned, as the D-25VF, the engine has l,000hr interval between major shop maintenance schedules. An alternative designation for the D-25V is TB-2BM. D-25V Nine-stage compressor, cannular combustor, single- stage compressor turbine, two-stage power turbine. Direct drive. Take-off 5,500 e.h.p.; pressure ratio 5-6:1; length 107-8in; weight 2,6451b. D-30P Two-shaft turbofan. The basic version is the 15,0001b D-30P powering the Tupolev Tu-134 series. D-30P Four-stage fan, ten-stage h-p compressor, annular combustor, two-stage h-p and l-p turbines. Take-off 15,0001b; bypass ratio 1:1; mass flow 2751b/sec; pressure ratio 18-6:1; length l56-8in; diameter 37-9in; weight 3,3501b. Flight-testing of the M53 began earlier this year in a Caravelle test-bed lillllllllliliiBI^M ^m§ i, j.i mm* 1 M^^HriUM lllllllllllis^«§ji i* *# • • •,. it ' a * -Wife ,* •F fm. ; ,A... if * •SwsMw 4y?a •MB •EMI ^^SkSKOKBHUM m tmlwMiiS^ft^"****:*»^ffil»|?'-*'Siwtl!****-*** 1 * vi m 111
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