Wright R-1300
The Wright R-1300 Cyclone 7 (internal name: Curtiss 957 ) was an air-cooled 7-cylinder radial engine with a compressor made by the American manufacturer Curtiss-Wright .
history
The R-1300 is essentially a one-star Wright R-2600 . The engine was produced in larger series, but was not widely used. Development began in 1942, but the engine could not be tested in the air until 1949. It was also manufactured under license by Kaiser-Frazer and later Lycoming .
The engine was installed in the North American T-28A Trojan and the Sikorsky UH-19 Chickasaw . It was also used in the Rockwell Thrush Commander S-2R agricultural aircraft , which was taken over by the Ayres company.
The R-1300-3 version was created for installation in helicopters, with an output reduced to 515 kW (700 hp).
The cylinders were made of steel and nitrided. They were cooled with the help of attached aluminum ribs. The cylinder heads were made of forged aluminum, from which the cooling fins milled were. The cylinder heads were shrunk onto the cylinders and screwed to them. Each cylinder head carried two valves, with the exhaust valve being sodium-cooled . The valve train itself consisted of a two-lane cam drum, from which the valves were operated via roller tappets, push rods and rocker arms . The pistons were made of high-strength forged aluminum and were internally cooled by spray oil. The crank mechanism consisted of an undivided main connecting rod forged from steel , to which six secondary connecting rods with an H cross-section were hinged. There were plain bearings used. The crankshaft was designed in two parts for the connecting rod assembly and was dynamically damped. Forged steel was used for the crankcase . The front part carried the reduction gear and, like the rear part with the compressor and the power take-offs, was made of a magnesium alloy. The engine was supplied with oil through dry sump lubrication . Bosch SF7LU-1 magnets provided the ignition .
Technical data (R-1300-1)
- Cylinder: 7, air-cooled
- Bore: 155.6 mm
- Stroke: 160.34 mm
- Displacement: 21.4 l
- Compression: 6.2: 1
- Gear ratio of the compressor: 7.21: 1
- Reduction of the propeller drive: 0.5625: 1
- Takeoff power: 588 kW (800 PS) at a speed of 2600 rpm in 1070 m
- Continuous output: 515 kW (700 PS) at a speed of 2400 rpm in 1525 m
- Carburettor: Stromberg P9DE1
- Diameter: 1281 mm
- Length: 1255 mm
- Dry weight: 461 kg
- Octane number requirement: 91/98 RON
