The Antarès was a conventionally laid out radial engine, with 14 cylinders in two rows. The crankcase was a barrel-shaped aluminium alloy casting, with an internal integral diaphragm which held the front crankshaft bearing. Forward of the diaphragm there was an integrally cast cam-gear case for the double track cam-rings. The reduction gear was housed under a domed casing attached to the front of the crankcase.
Flange-mounted steel barrels were bolted to the crankcase and enclosed with cast aluminium alloy, screwed-on, cylinder heads with integral cooling fins. The pistons were also made of aluminium alloy and had floating gudgeon pins. The fourteen pistons drove the double throw crankshaft via two channel-section master rods and twelve circular section auxiliary rods. The master rod had an integral, split type big-end. The crankshaft was machined from a single forging, with bolt-on balance weights.
The Antarès had a single pair of overhead inlet and exhaust valves per cylinder. The cam-rings drove roller tappets, mounted in the cam-case, which in turn operated rocker arms, fitted with ball bearings, via pushrods. The cam-rings were concentric with the crankshaft and driven via epicyclic gears. Most Antarès were conventionally aspirated via a single carburettor.
Length: 1,424 mm (56.06 in) - direct drive, 1,552 mm (61.10 in) - reduction gear
Diameter: 1,240 mm (48.82 in)
Dry weight: complete 448 kg (988 lb) - direct drive, 487 kg (1,074 lb) - reduction gear
Components
Valvetrain: one inlet and one exhaust overhead valve per cylinder, operated with rocker arms, pushrod driven via roller tappets bearing on a double track cam-ring
Fuel system: dual 75 mm (2.95 in) Zenith carburettors
Wikimedia Commons has media related to Lorraine 14.
^Revue de la Societe Generale Aeronautique(PDF) (in French). Paris: Societe Generale Aeronautique. November 1932. pp. 28–30. Retrieved 12 October 2014.
Revue de la Societe Generale Aeronautique(PDF) (in French). Paris: Societe Generale Aeronautique. November 1932. pp. 28–30. Retrieved 12 October 2014.
January 01, 1970
lorraine, antarès, french, cylinder, radial, aero, engine, built, used, 1930s, rated, range, antarès, type, cylinder, cooled, radial, aircraft, engine, national, origin, france, manufacturer, société, lorraine, argenteuil, paris, variants, lorraine, sirius, co. The Lorraine 14A Antares was a French 14 cylinder radial aero engine built and used in the 1930s It was rated in the 370 kW 500 hp range 14A Antares 14E Type 14 cylinder air cooled radial aircraft engine National origin France Manufacturer Societe Lorraine Argenteuil Paris Variants Lorraine Sirius Contents 1 Design and development 2 Variants 3 Specifications 3 1 General characteristics 3 2 Components 3 3 Performance 4 ReferencesDesign and development editThe Antares was a conventionally laid out radial engine with 14 cylinders in two rows The crankcase was a barrel shaped aluminium alloy casting with an internal integral diaphragm which held the front crankshaft bearing Forward of the diaphragm there was an integrally cast cam gear case for the double track cam rings The reduction gear was housed under a domed casing attached to the front of the crankcase Flange mounted steel barrels were bolted to the crankcase and enclosed with cast aluminium alloy screwed on cylinder heads with integral cooling fins The pistons were also made of aluminium alloy and had floating gudgeon pins The fourteen pistons drove the double throw crankshaft via two channel section master rods and twelve circular section auxiliary rods The master rod had an integral split type big end The crankshaft was machined from a single forging with bolt on balance weights The Antares had a single pair of overhead inlet and exhaust valves per cylinder The cam rings drove roller tappets mounted in the cam case which in turn operated rocker arms fitted with ball bearings via pushrods The cam rings were concentric with the crankshaft and driven via epicyclic gears Most Antares were conventionally aspirated via a single carburettor Variants edit14A 14Ac 14E 14LSpecifications editData from Societe Generale Aeronautique 1 General characteristics Type 14 cylinder two row radial piston engine Bore 140 mm 5 51 in Stroke 150 mm 5 91 in Displacement 32 326 L 1 972 7 cu in Length 1 424 mm 56 06 in direct drive 1 552 mm 61 10 in reduction gear Diameter 1 240 mm 48 82 in Dry weight complete 448 kg 988 lb direct drive 487 kg 1 074 lb reduction gear Components Valvetrain one inlet and one exhaust overhead valve per cylinder operated with rocker arms pushrod driven via roller tappets bearing on a double track cam ring Fuel system dual 75 mm 2 95 in Zenith carburettors Fuel type petrol Cooling system air cooled Reduction gear 0 647 1 Performance Power output 370 kW 500 hp at 1900 rpm Compression ratio 5 1 Specific fuel consumption 0 311 kg kW hr 0 511 lb hp hr Oil consumption 0 016 kg kW hr 0 026 lb hp hr References edit nbsp Wikimedia Commons has media related to Lorraine 14 Revue de la Societe Generale Aeronautique PDF in French Paris Societe Generale Aeronautique November 1932 pp 28 30 Retrieved 12 October 2014 Revue de la Societe Generale Aeronautique PDF in French Paris Societe Generale Aeronautique November 1932 pp 28 30 Retrieved 12 October 2014 Retrieved from https en wikipedia org w index php title Lorraine 14A Antares amp oldid 1126165116, wikipedia, wiki, book, books, library,
