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Anzani 10-cylinder
The Anzani 10 was a 1913 10-cylinder air-cooled radial aircraft engine. It powered several experimental aircraft and also the later production versions of the Caudron G.3 reconnaissance aircraft, the Caudron G.4 bomber/trainer and the first production Cessna, the Model AA.
==Design and development==
In the first decade of the 20th century Anzani developed his upright 3-cylinder 'W' type motorcycle engine, which powered Bleriot's successful Channel crossing flight of 1909, into a three-cylinder symmetric or 'Y' radial, and from that to a 6-cylinder double-row radial engine.
By 1912〔 he had built the Anzani 10, a 10-cylinder engine, air-cooled like its predecessors, which, like other Anzani engines, was made with different size cylinders. One of the more powerful versions produced about 110 hp (82 kW) from 12.1 litres,〔 a British-built Anzani 10 was rated at 125 hp〔''Flight'', 2 May 1914 p.474〕 and a smaller version with a displacement of 8.27 litres produced 80 hp (60 kW).〔 It was a double row engine, built with two rows of five cylinders separated along the crankshaft by about a cylinder radius, giving the engine a slimmer profile than other contemporary two-row radial engines. Each half had its own crankpin, 180° apart,〔(A History of Aeronautics Pt 4 Ch 3 )〕 with the connecting rods,of chrome nickel steel, broad and flat to bring the two halves close together.〔〔''Flight'', 24 January 1914 pp.97-8〕 Cylinder heads and pistons were made of cast iron, the latter machined inside and out and fitted with a pair of rings.〔 Oil was forced through the crankshaft to the crankpins, then moved under centrifugal force to the cylinders and pistons〔 from inside the crankcase which was a single light alloy casting.〔
Both inlet and exhaust valves were in the cylinder heads. The automatic inlet valves of earlier Anzani engines, opened by atmospheric pressure and closed by valve springs〔''Flight'', 5 July 1913 p.748〕 were retained, but fuel was fed from a mixing chamber in the crankcase via inlet tubes placed at the rear of the engine to avoid cooling of the mixture by the oncoming airflow.〔''Flight'', 4 January 1913 p.21〕 This arrangement placed the exhaust valves at the front of the engine, where they were operated from a cam in the rear of the crankcase via push rods and rockers.〔〔In some images of the rear of the engine, it is initially difficult to see the narrow pushods against the background of the broader inlet tubes, e.g. Fig 4 in ''Flight'' 4 January 1913, p.21〕 A single carburettor fed the crankcase chambers from below. Some versions used a single Gibaud magneto,〔 running at 3,000 rpm, though others built by British Anzani had a pair of Bosch magnetos,〔 running slower. Plugs (K.L.G. for the British variant〔) were mounted in the sides of the cylinder heads, sloping upwards to avoid plug fouling by lubricating oil.〔 The exhaust was collected by a prominent pair of semi-circular manifolds.
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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