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Contents

   



(Top)
 


1 Variants  





2 Specifications (14R-04)  



2.1  General characteristics  





2.2  Components  





2.3  Performance  







3 See also  





4 References  














SNECMA 14R






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From Wikipedia, the free encyclopedia
 


SNECMA 14R
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 14P and then the Gnome-Rhône 14R. There were several improvements such as the introduction of a longer crankshaft and crankcase with a centre bearing, an increase in cylinder capacity, and a two-speed compressor. These changes allowed the engine to deliver 1,400hp at take-off and 1,300hp at 1,500m (1st gear) and 1200hp at 4000m (2nd gear). This came at the cost of a much increased total weight. It was expected that further development, such as the introduction of higher grade fuels, would lead to a power output of 1,660hp at low altitude.

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[edit]

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)[edit]

Data from [2]

General characteristics

Components

Performance

See also[edit]

Related lists

References[edit]

  1. ^ Wilkinson, Paul H. (1946). Aircraft engines of the World 1946 (4th ed.). London: Sir Isaac Pitman & Sons Ltd.
  • ^ Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (3rd ed.). London: Sir Isaac Pitman & Sons Ltd.

  • Retrieved from "https://en.wikipedia.org/w/index.php?title=SNECMA_14R&oldid=1218674051"

    Categories: 
    1930s aircraft piston engines
    Aircraft air-cooled radial piston engines
    Gnome-Rhône aircraft engines
    Snecma aircraft engines
    Hidden categories: 
    Articles with short description
    Short description matches Wikidata
    Commons category link is on Wikidata
     



    This page was last edited on 13 April 2024, at 03:16 (UTC).

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