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Allison V-1710
The Allison V-1710 aircraft engine was the only indigenous US-developed V-12 liquid-cooled engine to see service during World War II. Versions with a turbosupercharger gave excellent performance at high altitude in the twin-engined Lockheed P-38 Lightning, and turbosuperchargers were fitted to experimental single-engined fighters with similar results. The US Army preference for turbosuperchargers early in the program meant that less effort was spent on developing suitable superchargers, and when smaller or lower-cost versions of the engine were desired, they generally had poor performance at higher altitudes. The V-1710 nevertheless gave excellent service when turbosupercharged, notably in the P-38 Lightning, which accounted for much of the extensive production run.
Design and Development - Turbocharger
Specifications
Type: Liquid-cooled V-12 piston engine
Manufacturer: Allison Engine Company
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First run: 1930
Number built: 70,000+
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General characteristics
Type: 12-cylinder supercharged liquid-cooled 60° "Vee" piston aircraft engine
Bore: 5.5 in (139.7 mm)
Stroke: 6.0 in (152.4 mm)
Displacement: 1,710 cu in (28 L)
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Length: 85.81 in (2,180 mm)
Width: 29.28 in (744 mm)
Height: 37.65 in (958 mm)
Dry weight: 1,395 lb (633.5 kg)
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Components
Valvetrain: Two intake and two exhaust valves per cylinder with sodium-cooled exhaust
valves, operated by a single gear-driven overhead camshaft per each bank of cylinders
Supercharger: Centrifugal-type, single-stage, 15-vane impeller, 10.25 in (260 mm) diameter
Fuel system: Bendix Stromberg carburetor with automatic mixture control
Fuel type: 100 octane
Oil system: Dry sump with one pressure and two scavenge pumps.
Cooling system: Liquid-cooled with a mixture of 70% water and 30% ethylene glycol,
pressurized.
Performance
Power output: 1,475 hp (1,100 kW) at 3,000 rpm
Specific power: 0.86 hp/cu in (39.3 kW/L)
Compression ratio: 6.65:1
Power-to-weight ratio: 1.05 hp/lb (1.76 kW/kg)
[Source - Wikipedia]
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