Avia Rk.17
| Rk.17 | |
|---|---|
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| Rk.17 in Letecké muzeum Kbely, Prague | |
| Type | 9-cylinder air-cooled radial |
| National origin | Czechoslovakia |
| Manufacturer | Avia (Avia akciova spolecnost pro prumysl letecky), Prague |
The Avia Rk.17 was a 9-cylinder radial aircraft engine, developed from the 7-cylinder Avia Rk.12, with a rated output of 270 kW (360 hp). The Rk.17 was one of Avia's own designs and was built in Czechoslovakia in the 1930s.
Design and development
As well as producing aircraft and building Hispano-Suiza and Lorraine aero-engines under licence, Avia also designed and built their own radial engines. The Rk.17 was a 9-cylinder supercharged model, rated at 360 hp. It was a nine-cylinder version of their Rk.12.[1]
It was a conventional air-cooled radial: nitrided steel barrels with integral fins were screwed into heat treated Y alloy heads. The pistons were also of heat treated Y alloy. The crankcase was cast from heat treated silumin alloy, with some minor parts using magnesium alloy. The single throw two piece crankshaft was linked to the pistons with an I-section Y alloy master rod, with a single piece big end, which carried the other eight piston rods.[1]
Applications
Specifications
Data from Jane's All the World's Aircraft 1938[1]
General characteristics
- Type: 9-cylinder air-cooled radial
- Bore: 130 mm (5.12 in)
- Stroke: 140 mm (5.51 in)
- Displacement: 16.72 L (1,020 cu in)
- Length: 1,065 mm (41.93 in)
- Diameter: 1,184 mm (46.61 in)
- Dry weight: 260 kg (573 lb) with ancillaries, without propeller hub
Components
- Valvetrain: one inlet and one exhaust valve per cylinder, operated by push-rods via rocker gear. Eight cam push-rod disc drive.
- Supercharger: impeller drive ratio 10.7:1
- Fuel system: single barrel Stromberg NAR80G carburettor
- Ignition system: Scintilla magnetos, automatic advance
- Fuel type: petrol, 85 Octane
- Oil system: dry sump, with one pressure and one scavenging pump
- Cooling system: air-cooled
- Reduction gear: direct drive
Performance
- Power output: rated maintained up to 2,750 m (9,000 ft), at 2,200 rpm 270 kW (360 hp)
- Power output: maximum continuous at 2,200 rpm 300 kW (400 hp)
- Power output: take-off at 2,020 rpm 330 kW (440 hp)
- Compression ratio: 6.4:1
- Specific fuel consumption: 255 g/(kW.h) (0.562 lb/(hp.h))
- Oil consumption: 8.7 g/(kW.h) (0.23 oz/(hp.h))
References
- ^ a b c Grey, C.G. (1972). Jane's All the World's Aircraft 1938. London: David & Charles. p. 31d. ISBN 0-7153-5734-4.
Further reading
- Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. p. 37d.