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Lorraine 14A Antarès

From Wikipedia, the free encyclopedia

14A Antarès
Lorraine 14E L'Aerophile January 1942.jpg
Type 14-cylinder air-cooled radial aircraft engine
National origin France
Manufacturer Société Lorraine, Argenteuil, Paris
Variants Lorraine Sirius

The Lorraine 14A Antarès was a French 14-cylinder radial aero engine built and used in the 1930s. It was rated in the 370 kW (500 hp) range.

Design and development

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.




Data 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


  • 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



  1. ^ Revue de la Societe Generale Aeronautique (PDF) (in French). Paris: Societe Generale Aeronautique. November 1932. pp. 28–30. Retrieved 12 October 2014.
This page was last edited on 15 January 2021, at 09:15
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