Daimler-Benz DB 605
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The Daimler-Benz DB 605 was a German aircraft engine, built during World War II . Developed from the Daimler-Benz DB 601 first produced in 1938, the DB 605 was used mainly in Messerschmitt Bf 109 and Bf 110 fighters. License-built versions of the DB 605 were used in the MC.205 Veltro, G.55 Centauro and some other Italian aircraft.
The inverted mounting of the cylinders provided better visibility for the pilot, a lower center of gravity, and improved access for maintenance. In the Bf 109, a cannon was mounted between the engine banks and fired through the propeller hub. The DB 605 used fuel injection instead of a carburetor, a great asset in combat because the engine did not cut out under negative g-forces.
Note: All power ratings in PS (metric horsepower). Unless otherwise noted takeoff/emergency power at sea level.
[edit] Production versions
- DB 605 A(M) Standard fighter engine, up to 1475 PS, 605 AM with MW50 system up to 1800 PS
- DB 605 AS(M) Altitude optimized version of 605 A using the larger DB 603 supercharger, up to 1435 PS, ASM with MW-50 system and up to 1800 PS
- DB 605 ASB(M) Altitude optimized late-war version of 605 AS using B4 fuel, ASBM with MW-50 system and up to 1800 PS
- DB 605 ASC(M) Altitude optimized late-war version of 605 AS using C3 fuel, ASCM with MW-50 system and up to 2000 PS
- DB 605 DM First DB 605 D version, standard MW-50 equipment, up to 1700 PS
- DB 605 DBM Improved 605 DM, standard MW-50 equipment, first version up to 1850 PS, later reduced to 1800 PS, B4 fuel
- DB 605 DCM Improved 605 DM, standard MW-50 equipment, up to 2000 PS, C3 fuel
- DB 610 Two DB 605 coupled to work on a single propeller shaft for use in Heinkel He 177
[edit] Prototype/pre-production versions
- DB 605 BS proposed version for twin-engined aircraft, derived from DB 605 AS
- DB 605 E proposed version for twin-engined aircraft, derived from DB 605 D
- DB 605 L Similar to 605 D but with two-stage supercharger, 2000+ PS
[edit] Engine Specifications (DB 605AM)
(also known as DB 605 G during development)
General characteristics
- Type: 12-cylinder liquid-cooled supercharged 60° inverted Vee aircraft piston engine
- Bore: 154 mm (6.06 in)
- Stroke: 160 mm (6.30 in)
- Displacement: 35.7 L (2,180 in³)
- Length: 2,303 mm (90.67 in)
- Diameter: 845 mm (33.27 in)
- Dry weight: 730 kg (1,642 lb)
Components
- Valvetrain: Two intake and two sodium-cooled exhaust valves per cylinder actuated via a single overhead camshaft per cylinder block.
- Supercharger: Single-stage variable-speed centrifugal type supercharger driven through a barometrically controlled clutch; MW50 injection into the supercharger intake.
- Fuel system: Direct fuel injection
- Oil system: Dry sump with one pressure and two scavenge pumps
- Cooling system: Liquid-cooled, pressurized
Performance
- Power output:
- 1,325 kW (1,800 PS - 1,775 hp) at 2,800 rpm for takeoff with MW-50 injection
- 1,250 kW (1,700 PS - 1,675 hp) at 2,800 rpm at 4,000 m (13,120 ft) for maximum power with MW-50 injection
- 795 kW (1,080 PS - 1,065 hp) at 2,300 rpm at 5,500 m (18,000 ft) for max continuous
- Specific power: 35.0 kW/L (0.77 hp/in³)
- Compression ratio: 7.5/7.3:1 with 87-octane fuel; 8.5/8.3:1 with 100-octane fuel
- Power-to-weight ratio: 1.68 kW/kg (1.02 hp/lb)
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