Curtiss V-1570 Conqueror

V-1570
	A V-1570-53 at the National Air and Space Museum.
Type	V12 piston engine
Manufacturer	Curtiss Aeroplane and Motor Company
First run	1926

The Curtiss V-1570 Conqueror was a V12 liquid-cooled aircraft engine. Representing a more powerful version of the Curtiss D-12, the engine entered production in 1926 and flew in numerous aircraft.^[1]

Design and development

Designed in 1924 as a military successor to the Curtiss D-12, initially named the Conqueror, it was later given the military designation of V-1570 based on its displacement of 1,570 cubic inches (26 L). The engine featured open-ended cylinder liners (advanced technology for the period) and pressurized liquid cooling. Developments including the use of a supercharger gradually increased power output until reliability problems due to overheating and coolant leaks became apparent. Military funding for further development of the Conqueror was cut in 1932, efforts by Curtiss to market the engine for civil airliners failed and the line was dropped from production.

Variants

V-1570-1
V-1570-5
V-1570-7
GV-1570-7: geared -7
V-1570-9
V-1570-11
V-1570-13
V-1570-15
SV-1570-15
V-1570-17
V-1570-23
V-1570-25
V-1570-27
V-1570-29
V-1570-33
V-1570-53
V-1570-55
V-1570-57
V-1570-59
V-1570-61
V-1570-79
GIV-1570-FM
V-1570-C
V-1570-F
GIV-1570C

Applications

Other applications

Mormon Meteor III (custom Bonneville salt flat race car)

Specifications (V-1570 direct drive)

Data from Grey and Gunston.^[2]^[1]

General characteristics

Type: V-12 liquid-cooled aircraft piston engine
Bore: 5+1⁄8 in (130 mm)
Stroke: 6+11⁄32 in (161 mm)
Displacement: 1,570.4 cu in (25.7 L)
Length: 64 in (1,600 mm)
Width: 26+5⁄16 in (668 mm)
Height: 39+1⁄16 in (992 mm)
Dry weight: 835 lb (379 kg)

Components

Valvetrain: Inlet and exhaust overhead camshafts operating two exhaust and two inlet valves per cylinder, via 'T' head cam followers.
Fuel system: Two Stromberg NA-Y6-O carburetors
Oil system: Dry sump, pressure feed and spray with scavenge.
Cooling system: Liquid-cooled (water or chemical coolant)
Reduction gear: Direct-drive
Ignition system: One Scintilla magneto and two distributors

Performance

Power output: 600 hp (450 kW) at 2,400 rpm (direct-drive)
Specific power: 0.43 hp/in³ (19.6 kW/L)
Compression ratio: 6.1:1
Specific fuel consumption: 0.53 lb/(hp⋅h) (0.32 kg/kWh)
Oil consumption: 0.02 lb/(hp⋅h) (0.012 kg/kWh)

References

Notes

^ ^a ^b Gunston 1989, p. 46.
^ Grey 1931, p. 72.

Bibliography

Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
Grey, C.G. Jane's all the World's Aircraft 1931 London, England. Sampson Low, Marston & Company Limited

[Gunston46-1] Gunston 1989, p. 46.

[2] Grey 1931, p. 72.

[1]

[2]