Curtiss V-1570

The Curtiss V-1570 Conqueror was a 12-cylinder vee 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]

V-1570
A V-1570 on display at the National Museum of the United States Air Force.
Type V12 piston engine
Manufacturer Curtiss Aeroplane and Motor Company
First run 1926

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 / GV-1570 geared)

Data from Jane's all the World's Aircraft 1931[2]

General characteristics

  • Type: V-12 liquid-cooled aircraft piston engine
  • Bore: 5.125 in (130.2 mm)
  • Stroke: 6.125 in (155.6 mm)
  • Displacement: 1,570.4 cu in (25.734 l)
  • Length: 64 in (1,600 mm) (direct-drive)
68.84375 in (1,748.631 mm) (geared)
  • Width: 26.3125 in (668.34 mm)
  • Height: 39.0625 in (992.19 mm)
  • Dry weight: 835 lb (379 kg) (direct-drive)
925 lb (420 kg) (geared)

Components

  • Valvetrain: Inlet and exhaust overhead camshafts operating 2 exhaust and 2 inlet valves per cylinder, via 'T' head cam followers.
  • Fuel system: Two Stromberg NA-Y6-O carburettors
  • Oil system: Dry sump, pressure feed and spray with scavenge.
  • Cooling system: Liquid-cooled (water or chemical coolant)
  • Reduction gear: direct-drive, 2:1 or 7:5
  • One Scintilla magneto and two distributors

Performance

  • Power output: 600 hp (450 kW) at 2,400 rpm (direct-drive)
600 hp (450 kW) at 2,450 rpm (geared)
  • 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/kW/h)
  • Oil consumption: 0.02 lb/hp/h (0.012 kg/kW/h)

See also

Related development

Comparable engines

Related lists

References

Notes
  1. Gunston 1989, p.46.
  2. Grey, C.G., ed. (1931). Jane's all the World's Aircraft 1931. London: Sampson Low, Marston & company, ltd. p. 72d.

Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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