Gnome-Rhône 14N

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GR 14N 49b.JPG
Type Radial engine
Manufacturer Gnome et Rhône
First run 1937

The 14N was a 14-cylinder two-row air-cooled radial engine designed and manufactured by Gnome-Rhône. A development of the pre-war Gnome-Rhône 14K, the 14N was used on several French and German aircraft of World War II.

Design and development[edit]

Facing criticisms over the 14K's reliability, Gnome-Rhône undertook a major upgrade of its 14-cylinder design, using different materials for the pistons and valves, and enlarging cooling surfaces by 39%.

The new 14N was introduced in 1937 and was quickly adopted on several aircraft models. In 1939, minor improvements allowed Gnome-Rhône to increase the compression ratio from 6.1:1 to 6.8:1, which resulted in increased power for wartime production aircraft.

The 14N was further developed into the Gnome-Rhône 14R featuring a 2-stage supercharger, but this type was not widely used until after World War II as production of improved engines was prohibited by the terms of the armistice with Germany.

Postwar the 14R was developed into a 28 cylinder high capacity engine as the Gnome-Rhône 28T-1, essentially two 14R-24 engines back to back driving co-axial contra-rotating propeller shafts.[1]


Data from:Aircraft engines of the World 1945,[2] Aircraft engines of the World 1946[1]

LH rotation, 780 kW (1,050 hp).
RH rotation version of -44.
LH rotation, 880 kW (1,180 hp).
RH rotation version of -48.
LH rotation, 1,000 kW (1,400 hp).
LH rotation, 930 kW (1,250 hp).
RH rotation version of -54.
LH rotation, 880 kW (1,180 hp).
RH rotation version of -58.
Improved higher performance using 92 Octane fuel. 14N with 2-speed supercharge (6.5:1 and 9:1), LH rotation, 1,190 kW (1,590 hp) for take-off.
RH rotation version of14R-4.
LH rotation, 1,200 kW (1,600 hp).
RH rotation version of 14R-24.
28 cylinder, double 14R-24 with co-axial contra-rotating propeller shafts, direct fuel injection, 2-speed supercharger, 77.4 l (4,720 cu in) displacement, delivering 2,400 kW (3,200 hp) for take-off using 100/130 octane fuel.[1]


Specifications (14N-48)[edit]

Data from Aircraft engines of the World 1945[2]

General characteristics

  • Type: Fourteen-cylinder two-row air-cooled piston engine
  • Bore: 146 mm (5.75 in)
  • Stroke: 165 mm (6.50 in)
  • Displacement: 38.67 l (2,360 cu in)
  • Length: 1,480 mm (58.27 in)
  • Diameter: 1,290 mm (50.79 in)
  • Dry weight: 620 kg (1,370 lb)



  • Power output:
  • Take-off: 880 kW (1,180 hp) at 2,650 rpm
  • Military: 790 kW (1,060 hp) at 2,400 rpm at 3,900 m (12,800 ft)
  • Cruise: 630 kW (850 hp) at 2,100 rpm at 3,900 m (12,800 ft)
  • Specific power: 22.45 kW/l (0.49 hp/in³)
  • Compression ratio: 6.8:1
  • Power-to-weight ratio: 1.4 kW/kg (0.85 hp/lb)

See also[edit]


  1. ^ a b c Wilkinson, Paul H. (1946). Aircraft engines of the World 1946 (4th ed.). London: Sir Isaac Pitman & Sons Ltd. 
  2. ^ a b Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (3rd ed.). -New York: Paul H. Wilkinson. 
  • Danel, Raymond and Cuny, Jean. L'aviation française de bombardement et de renseignement 1918-1940 Docavia n°12, Editions Larivière