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ALLISON V-3420

In 1937, at the behest of the United States Army Air Corps, the Allison Engine Company agreed to design and build a large-displacement high-power aircraft engine. The resulting V-3420 was essentially a pair of 12-cylinder Allison V-1710 engines mated to a common crankcase with a 30° angle between the inner cylinder banks. The crankshafts of the two V-1710 engines were geared together to drive a common propeller shaft. Most V-3420 parts were interchangeable with those for V-1710-E and -F engines.

The V-3420 had a power-to-weight ratio of 1.6 kW/kg or 1 hp/lb, excellent for its time. It was envisioned as a powerful yet compact engine for several advanced Air Force projects of the day, including the Douglas XB-19, the Boeing XB-39 Superfortress, the Lockheed XP-58 Chain Lightning, and the General Motors P-75 Eagle. As none of these designs reached full-scale production, only about 150 V-3420s were built.


Variants
V-3420-A16R (-11)

V-3420-A16L (-13)
Left hand rotation of propeller, single-stage supercharger with single-stage turbocharger and intercooler

V-3420-A18R (-17)

V-3420-A24
Supercharger ratio 7.2:1

V-3420-B (-23)
Similar to the -A but with mechanically driven supercharger in two variable speed stages.


Specifications: V-3420-A18R (-17)
General characteristics
  • Type: 24-cylinder turbosupercharged double-"Vee" liquid-cooled piston engine
  • Bore: 5.5 in (139.7 mm)
  • Stroke: 6 in (152.4 mm)
  • Displacement: 3,420 in3 (56 L)
  • Length: 97.7 in (2,482 mm)
  • Width: 60.0 in (1,421 mm)
  • Height: 38.7 in (863 mm)
  • Dry weight: 2,655 lb (1,204 kg)

Components
  • Valvetrain: Single overhead camshaft per 6-cylinder block, two intake and two exhaust valves per cylinder, sodium-cooled exhaust valves.
  • Supercharger: Single-speed one-stage gear-driven supercharger
  • Turbocharger: General Electric turbocharger with intercooler
  • Fuel system: Bendix-Stromberg PR-58B3 three-barrel injection-type downdraught with automatic mixture control.
  • Fuel type: 100/130 Octane
  • Oil system: Pressure fed at 60-70 psi (4.2 - 4.9 kg/m²)
  • Cooling system: Liquid-cooled with a mixture of 70% water and 30% ethylene glycol, pressurized.

Performance:
  • Horsepower:
    • Take-Off: 2,600 hp (1,940 kW) at 3,000 rpm at 46.0 inHg / +8.0Lb boost for 15 minutes
    • Military: 2,600 hp (1,940 kW) at 3,000 rpm at 25,000 ft (7,625 m) for 15 minutes
    • Normal: 2,100 hp (1,565 kW) at 2,600 rpm at 25,000 ft (7,625 m) maximum continuous power
    • Maximum Cruising: 1,575 hp (1,175 kW) at 2,300 rpm at 25,000 ft (7,625 m)
  • Specific power: 0.76 hp/cu in (34.6 kW/l)
  • Compression ratio: 6.65:1
  • Specific fuel consumption: 0.41 lb/hp/hr (11 g/kW/hr)
  • Oil consumption: 0.025 lb/hp/hr (138g/kW/hr)
  • Power-to-weight ratio: 1.0 hp/lb (1.64 kW/kg)

[Source - Wikipedia]
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