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From Wikipedia, the free encyclopedia

SNECMA 14R
Gnome et Rhône 14R 04-05 - Musée Safran 07.jpg
Type 14 cylinder two-row air-cooled radial piston engine
National origin France
Manufacturer Gnome-Rhône / SNECMA
Major applications Breguet Br 500 Colmar
Developed from Gnome-Rhône 14N

The SNECMA 14R was a 14-cylinder two-row air-cooled radial engine developed in France just prior to the start of World War II from the Gnome-Rhône 14N. The 14N radial engine was itself an improved version of the popular pre-war Gnome-Rhône 14K Mistral Major series; designed and manufactured by Gnome et Rhône, a major French aircraft engine manufacturer whose origins pre-date the First World War.

The improved 14R was initially known as the Gnome-Rhône 14R. With the Fall of France, engine development was stopped under the occupation. After the war, development recommenced; however production of this engine after 1945 was transferred to the newly formed SNECMA and the engine was renamed the SNECMA 14R.

Variants

14R-04
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.
14R-05
RH rotation version of 14R-4.
14R-08
RPM increased from 2,400 to 2,600 improving power output. LH rotation.
14R-09
RH rotation version of 14R-08
14R-24
LH rotation, 1,200 kW (1,600 hp).
14R-25
RH rotation version of 14R-24.
14R-26
LH rotation, 1,200 kW (1,600 hp).
14R-27
RH rotation version of 14R-26.
14R-28
LH rotation, 1,200 kW (1,600 hp).
14R-29
RH rotation version of 14R-28.
14R-32
LH rotation
14R-100
14R-200
LH rotation
14R-201
RH rotation
14R-210
28T-1
28 cylinder, double 14R-24 engines placed back-to-back 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 (14R-04)

Data from [2]

General characteristics

  • Type: 14 cylinder two-row air-cooled radial piston engine
  • Bore: 146 mm (5.75 in)
  • Stroke: 165 mm (6.50 in)
  • Displacement: 38.7 l (2,361.62 cu in)
  • Length: 1,635 mm (64.37 in)
  • Diameter: 1,297 mm (51.06 in)
  • Dry weight: 819 kg (1,805.59 lb)
  • Frontal Area: 1.33 m2 (14.3 sq ft)

Components

  • Valvetrain: Single inlet and exhaust valves operated by rockers and pushrods
  • Supercharger: Gear-driven 2-speed supercharger at 6.5:1 and 9.0:1 ratios
  • Fuel system: 1x Bronzavia updraught carburettor with automatic boost and altitude control
  • Fuel type: 92 Octane gasoline
  • Oil system: Pressure fed at 480 kPa (70 psi)
  • Cooling system: Air-cooled with baffles
  • Reduction gear: Planetary / epicyclic bevel reduction gearing at 0.67:1 ratio
  • Starter: Air equipment electric inertia starter
  • Ignition: 2 x R.B. magnetos, 2 x 18 mm (0.71 in) short reach spark plugs per cylinder fed by a shielded ignition harness.

Performance

  • Power output:
  • Take-off:1,590 hp (1,185.66 kW) at 2,600 rpm at 1,180 mm (46.46 in) Hg boost with 100 octane fuel
    • Military, low:1,660 hp (1,237.86 kW) at 2,600 rpm at 1,000 m (3,280.84 ft)
    • Military, high:1,580 hp (1,178.21 kW) at 2,600 rpm at 5,500 m (18,044.62 ft)
    • Normal, low:1,320 hp (984.32 kW) at 2,400 rpm at 2,100 m (6,889.76 ft)
    • Normal, high:1,230 hp (917.21 kW) at 2,400 rpm at 6,000 m (19,685.04 ft)
  • Specific power: 31.85 kW/l (0.7 hp/cu.in)
  • Compression ratio: 6.8:1
  • Specific fuel consumption: 0.292 kg/kW/hr (0.48 lb/hp/hr)
  • Oil consumption: 0.0067 kg/kW/hr (0.011 lb/hp/hr)
  • Power-to-weight ratio: 1.494 kW/kg (0.909• hp/lb)
  • B.M.E.P.: 1,470 kPa (213 psi)
  • 14R-05 propeller rotates in opposite direction

See also

Related lists

References

  1. ^ Wilkinson, Paul H. (1946). Aircraft engines of the World 1946 (4th ed.). London: Sir Isaac Pitman & Sons Ltd.
  2. ^ Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (3rd ed.). London: Sir Isaac Pitman & Sons Ltd.
This page was last edited on 23 December 2020, at 19:10
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