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Aviation History
1957
1957 - 1036.PDF
126 FLIGHT, 26 July 1957 AERO ENGINES 1957 . . . Turbomeca Turmo III. Free-turbine engine. Single transonic axial compressor stage followed by single centrifugal stage, annular combustion chamber, two-stage compressor turbine and independent single-stage power turbine. Overall width, 29.4in; overall height, 22.25in; overall length, 65.6in; dry weight, 5301b; mass flow, about 10.6 Ib/sec; pressure ratio, about 5.1:1; maximum rating, 750 h.p. at 34,500 r.p.m. (6,000 output r.p.m.) with s.f.c. of 0.77. A take-off rating of 900 h.p. with a maximum overload of 1,000 h.p., is foreseen^ for the near future. Turbo meca Astazou. Single-shaft turboprop. Single transonic axial compressor stage followed by single centrifugal stage, annular combustion chamber and multi-stage turbine. Overall diameter, 18.1in; length as shown, about 69in; dry weight, 245 Ib; mass flow and pressure ratio, not available; maximum rating, 320 h.p. at unstated r.p.m. with s.f.c. of 0.72 (this power is limited by reduction-gear capacity and is available up to92degF, or up to a height of 15,000ft at Mach 0.45). Turbomica Bastan. Single-shaft turboprop. Single transonic axial compressor stage followed by single centrifugal stage, annular combustion chamber and multi-stage turbine. Overall diameter, 21.6in; length as depicted, 60.9m; dry weight, with propeller but without oil-cooler, 585 Ib, or 397 lb without propeller; mass flow and pressure ratio, not available; max. rating, 650 s.h.p. at 33,000 r.p.m. (1,790 propeller r.p.m.) with s f.c. of 0.73, available up to 14,800ft at Mach 0.4. Turbomeca Palouste IV. Air compressor. Single centrifugal compressor, annular combustion chamber and two-stage turbine. Overall height as depicted, about 34in; width, about 21.6in; overall length, 52.3in; dry weight, 198 Ib; pressure ratio, 3.7:1; maximum output, 2.51 Ib/sec of air at 41.2 Ib/sq in gauge at 34,000 r.p.m. with fuel consumption of 265 Ib/hr; max. cont., 2.4 Ib/sec. Turbomexa Tramontane. Air compressor. Single centrifugal compressor, annular combustion chamber and two-stage turbine. Overall diameter, 22.75in; length, excluding tail.cone, 47.3in; dry weight, 370 Ib: mast flow, about 16.7 Ib/sec; pressure ratio, 3.5:1; maximum output, 5.5 Ib/sec of air at about 38 Ib/sq in gauge at 22,600 r.p.m. with fuel consumption of 680 Ib/hr; max. cont., 5.1 Ib/sec. 320 h.p., and the engine weight is 243 lb. Artouste Us have also flownin the S-59 and XH-13F helicopters in the U.S.A. An advanced derivative is the Artouste III which is the superchargedderivative of the earlier unit. The new engine has yet to fly, but it has recorded from 600 to 700 b.h.p. on numerous bench trials. Turmo. The engine illustrated is the latest of the company's free-turbine units and it can be regarded either as a supercharged Turmo II or a free-turbine Arbizon. Applications include new projects by Sud-Aviation and Breguet. Marcadau. This name applies to the Artouste II turboshaft enginefitted with a reduction gearbox and equipped as a turboprop. The powerplant weighs 350 lb without cowling or propeller, and is fitted tothe Cessna L-19C and the Farfadet convertiplane. Astazou. About a year ago Turbomeca started from scratch on anew series of engines incorporating all the experience gained with earlier units and designed to advanced techniques. These extremely attractiveand refined powerplants at present comprise the Astazou and Bastan turboshaft engines, and other engines designed to the new techniquesmay be expected to appear. Development of the Astazou has been straightforward and prototypesare about to run on the bench. The basic gas-producer section is extremely minute, being dwarfed by the reduction gear and two-bladeRatier propeller. A row of miniature accessories is carried around the back of the main intake casting. Bastan. Most powerful of the company's turboshaft engines, theBastan is the second of the "new generation" of highly efficient small turbines. Bench trials should be well advanced by the end of the yearand development is taking place against a prototype contract. At the front is the two-stage reduction gear, contained within a seriesof intake castings around the back of which is a peripheral row of gear- trains for driving the accessories. Typical equipment includes a Ratier-Figeac control unit, a Labinal 2.5 kW starter/generator and a three-blade constant-speed hydraulic propeller of 9ft 3in diameter, the pressureoil for which is tapped from the engine system. Compressed air can be tapped from the main casing, and a 15 h.p. mechanical drive is available,turning at up to 6,810 r.p.m. The Bastan has been selected to power the M.S. 1500 Epervier, the S.O. 1100 Fonceur and Super Broussard 02.Future developments are expected to lead to a maximum rating of 750 h.p. with an s.f.c. of 0.77, largely by raising the top temperature. Soulor. First shown at the 1955 Paris Salon, the Soulor is a ducted-fan engine with a maximum thrust of 705 lb. It was described and illustrated in our 1956 engine review. It is at present being furtherdeveloped as one of the engines of the new high-efficiency generation. Palouste. The engine illustrated is the latest of a series of turbo-compressor engines which are in production as the powerplant of the S.O. 1221 Djinn helicopter. Compared with its predecessors, thePalouste IV has a redesigned turbine-end giving better operating charac- teristics. The engines are delivered as complete powerplants which arereadily interchangeable in the field. Starting can be effected either by a hand-crank or by an electric motor or a small two-stroke piston engine.A sonic "flow-limiter" controls the output from the single pipe- connection above the main casing. Autan. Embodying a supercharging axial stage, characteristic of thegeneration of engines introduced in 1955, the Autan can be regarded as a supercharged Palouste IV with correspondingly greater output andefficiency. In appearance it is much like the Arbizon, and it provides as output of 3 lb of air per second, at a pressure ratio of 5.1 : 1 at 34,500r.p.m. The overall diameter is 16in and the weight 260 lb. It is worth noting that the Soulor ducted-fan unit is virtually an Autan in whichthe bleed air, instead of being extracted through a pipe, is expelled as a •propulsive jet. Tramontane. This engine is a natural development, in that it is anair-compressor with a centrifugal impeller of Marbor6 size. It is in an early stage ot development and its existence was only made public twomonths ago. Unlike the previous compressors, air is supplied from two outlets, one on each side of the main casing. ITALY AGUSTA. Meccanica Verghem Agusta, Gallarate (Prov. Varese).Long established in the automotive field, Agusta entered aviation as a licence-producer of Bell helicopters, of which more than 250 have been Agusta G.A.70/V. Piston engine for helicopters. Horizontally opposed four-cylinder engine mounted with crankshaft ver- tical, with float-chamber car- burettor, dual ignition and electric starter; gearbox or fan not shown. Overall width, 28.9in; height as shown, 22.8m: length, front to rear over car- burettor, 21.25in; swept volume, 140.4 cu in; dry weight, 147.7 1b; maximum rating, 72 h.p. at 3,100 r.p.m. at engine shaft.
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