BMW 132

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The BMW 132 was a nine-cylinder Radial engine Aircraft engine produced by BMW starting in 1933.

Contents

Design and development


BMW took over the license for manufacturing air-cooled radial engines from US aircraft manufacturer Pratt & Whitney on 3 January 1928. The nine-cylinder model Pratt & Whitney Hornet was initially manufactured virtually unchanged under the designation BMW Hornet. Soon BMW embarked on its own development. The result was the BMW 132 that went into production in 1933, which was essentially an improved version of the Hornet engine. A number of different versions were built. Aside from the carburettor designs used mainly in civilian aircraft, versions with direct fuel injection were manufactured for the Germany Luftwaffe. The engines had a Engine displacement of 27.7 liters and generated up to 1,200 bhp (890 kW), depending on model.

The 132 found widespread use in the Cargo aircraft role, remaining the primary powerplant of the Junkers Ju 52 for much of its life, turning the BMW 132 into one of the most important aeroengines for civilian aircraft during the 1930s.

Numerous pioneering flights were undertaken with the BMW 132. The most impressive was the first direct flight from Berlin to New York in a Focke-Wulf Fw 200 equipped with four BMW 132 engines. It covered the distance to New York in 24 hours and 57 minutes on 10 August 1938.

Variants


  • 132A - 725 hp (541 kW)
  • 132T - 730 hp (544 kW) , 830 hp (619 kW)
  • 132N - 865 hp (645 kW) , 1,000 hp (746 kW)
  • 132Dc - 880 hp (656 kW)
  • 132De - 880 hp (656 kW)
  • 132K - 960 hp (716 kW) , 970hp (723 kW)

Applications


  • Arado Ar 196
  • Arado Ar 197
  • Blohm & Voss Ha 140
  • Blohm & Voss BV 141
  • Heinkel He 114
  • Heinkel He 115
  • Henschel Hs 123
  • Junkers Ju 160
  • Junkers Ju 52
  • Junkers Ju 86
  • Junkers W34

Specifications (BMW 132 Dc)

Data from [1]

General characteristics
  • Type: Nine-cylinder single-row supercharged air-cooled Radial engine
  • Bore: 155.5 mm (6.12 in)
  • Stroke: 162 mm (6.38 in)
  • Displacement: 27.7 l (1,690 in³)
  • Length: 1,411 mm (55.55 in)
  • Diameter: 1,380 mm (54.33 in)
  • Dry weight: 525 kg (1,157 lb)
<h3>Components
  • Valvetrain: Two Overhead valve per cylinder
  • Supercharger: Single-speed Centrifugal type supercharger
  • Fuel system: Hobson Carburetor
  • Fuel type: 87 Octane rating Gasoline
  • Cooling system: Air-cooled
  • Reduction gear: Farman Aviation Works Epicyclic gearing, 1.61:1
<h3>Performance
  • Power output:
    • 589 kW (789 hp) for takeoff
    • 581 kW (779 hp) at 2,290 rpm at 2,900 m (9,515 ft)
  • Specific power: 21.26 kW/l (0.47 hp/in³)
  • Compression ratio: 6.5:1
  • Brake specific fuel consumption: 322 g/(kW•h) (0.53 lb/(hp•h))
  • Oil consumption: 8-11 g/(kW•h) (0.21-0.28 oz/(hp•h))
  • Power-to-weight ratio: 1.12 kW/kg (0.68 hp/lb)

See also

Related development

Related lists

  • List of aircraft engines

References

  1. Tsygulev (1939). Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv (Lang-ru). Moscow: Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR. http://base13.glasnet.ru/text/aviamotory/t.htm. 

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