Salmson air-cooled aero-engines
Between 1920 and 1951 the Société des Moteurs Salmson in France developed and built a series of widely used air-cooled aircraft engines.[1]
Design and development
After their successful water-cooled radial engines, developed from 1908 to 1918, Salmson changed their focus to air-cooling to reduce weight and increase specific power (power per unit weight). The majority of the engines produced by Salmson were of radial type with a few other arrangements such as the Salmson T6.E. In common with other engines produced by this manufacturer, the air-cooled radial engines featured the unorthodox Canton-Unné internal arrangement that dispensed with a master rod in favour of a cage of epicyclic gears driving the crankpin. Production ended in 1951 with the liquidation of the manufacturing company.
British Salmson
The 3,7 and 9 cylinder Salmsons were license-built in Great Britain, during the 1920s and 1930s, by the British Salmson engine company as the British Salmson AD.3, British Salmson AC.7, British Salmson AC.9, and British Salmson AD.9.
Salmson post-WWI engines
In common with several other French aero-engine manufacturers Salmson named their engines with the number of cylinders then a series letter in capitals followed by variant letters in lower-case. Engines not included in the 1932 table which follows are listed here: Script error: No such module "Template wrapper".Script error: No such module "Check for unknown parameters".
Salmson air-cooled engines available in 1932 are listed here[5]
Applications
Nine cylinder engines
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Seven cylinder engines
7AC
- Albert A-61
- Caudron C.191&2
- Caudron C.220
- Caudron C.270
- Dewoitine D.480
- Farman F.234
- Farman F.280
- Farman F.352
- Hanriot H.411
- Kellner-Béchereau 23
- Morane-Saulnier MS.132
- Morane-Saulnier MS.148
- Potez 36/5
Five cylinder engines
5Ap
5Aq
5AC
Specifications (9 Ab)
Data from Tsygulev[6]
General characteristics
- Type: Nine-cylinder single-row supercharged air-cooled radial engine
- Bore: 125 mm (4.92 in)
- Stroke: 170 mm (6.69 in)
- Displacement: 18.765 L (1,145 in³)
- Length: 1,000 mm (39.37 in)
- Diameter: 1,180 mm (46.46 in)
- Dry weight: 265 kg (584 lb)
Components
- Valvetrain: Two overhead valves per cylinder
- Supercharger: Single-speed centrifugal type supercharger
- Fuel system: Zenith 42D carburetor
- Cooling system: Air-cooled
Performance
- Power output: 191 kW (256 hp) at 1,780 rpm for takeoff
- Specific power: 10.18 kW/L (0.22 hp/in³)
- Compression ratio: 5:1
- Specific fuel consumption: 328 g/(kW•h) (0.54 lb/(hp•h))
- Oil consumption: 19 g/(kW•h) (0.49 oz/(hp•h))
- Power-to-weight ratio: 0.72 kW/kg (0.44 hp/lb)
See also
Notes
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References
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- Lumsden, Alec. British Piston Engines and their Aircraft. Marlborough, Wiltshire: Airlife Publishing, 2003. Template:ISBN.
- Cuny, Jean. "Latécoère - Les Avions et Hydravions".Paris. Docavia/Editions Lariviere. 1992. Template:ISBN