Lycoming R-680
| Lycoming | |
|---|---|
 |
|
| R-680 | |
| Production period: | 1929 – unknown |
| Manufacturer: | Lycoming |
| Working principle: | Otto |
| Motor design: | Radial engine |
| Drilling: | 117 mm |
| Hub: | 114 mm |
| Displacement: | 11150 cm 3 |
| Mixture preparation: | Carburetor |
| Engine charging: | no |
| Cooling system: | Air cooling |
| Power: | 165 - 210 kW |
| Dimensions: | 224 - 234 kg |
| Previous model: | none |
| Successor: | none |
The Lycoming R-680 is a nine-cylinder radial engine made by the US manufacturer Lycoming , which was used to power numerous light aircraft in the 1930s and 1940s.
history
The R-680 was created in early 1929, right after Lycoming was taken over by the Auburn Automobile Company , a company owned by industrialist Errett Lobban Cord . Up until then, Lycoming had focused on vehicle engines . The R-680 was the company's first aircraft engine . The engine , which was designed to be conservative in its design features, quickly became distinguished by its exceptional reliability. The output of the various construction stages was between 200 PS (147 kW ) and 285 PS (210 kW). Production continued until the end of the Second World War and over 26,000 were built.
variants
The series versions of the engine that were still produced in 1945 could be divided into two groups: the R-680-E and the R-680-B4E series. Both versions are the same in the essential construction details, which ensures that the engine parts can be largely exchanged. The R-680-E version can be equipped with adjustable or fixed propellers , while the R-680-B4E was offered as a version for training aircraft with a front exhaust manifold ring and engine covers without cylinder cooling air duct.
| Parameter | Data R-680-B4E | Data R-680-E3A (E series) |
|---|---|---|
| Hub | 114 mm | |
| drilling | 117 mm | |
| Displacement | 11.15 L (680.4 cubic inches ) | |
| compression | 5.5: 1 | 7: 1 |
| Valves | One inlet and one outlet valve per cylinder made of tungsten steel, solid inlet valve, outlet valve with hollow shaft ( filled with sodium for better cooling ) |
|
| Diameter ü. a. | 1105 mm | |
| Length ü. a. | 941 mm | |
| Reduction motor propeller | direct (counter-clockwise rotation) | |
| Mass (dry) | 223.5 kg | 233.9 kg |
| Octane number | 73 | 87 |
| Continuous output (at sea level) | 225 hp at 2100 min -1 | 285 hp at 2200 min -1 |
literature
- Bill Gunston: World Encyclopaedia of Aero Engines , Patrick Stephens Ltd., 3rd updated edition, 1995, ISBN 1-85260-509-X , p. 101
- Leonard Bridgman (Ed.): Jane's All The World's Aircraft 1945-1946. Samson Low, Marston & Company, Ltd., London 1946, p. 78d f.
Individual evidence
- ^ A b Leonard Bridgman: Jane's All The World's Aircraft 1945-1946 . Samson Low, Marston & Company, Ltd., London 1946, p. 79 (English).
