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|Preserved BMW 132E|
|Major applications||Junkers Ju 52|
|Developed from||Pratt & Whitney R-1690 Hornet|
|Developed into||BMW 114|
Design and developmentEdit
BMW took over a license for manufacturing air-cooled radial engines from Pratt & Whitney on 3 January 1928. The nine-cylinder model Pratt & Whitney R-1690 Hornet was initially manufactured virtually unchanged under the designation BMW Hornet.
Soon BMW embarked on its own development. The result was the BMW 132, essentially an improved version of the Hornet engine, that went into production in 1933. A number of different versions were built; aside from the carburetor designs used mainly in civilian aircraft, versions with direct fuel injection were manufactured for the German Luftwaffe. The engines had a displacement of 27.7 L (1,690 cu in) and generated up to 960 PS (950 hp; 710 kW) depending on model.
The 132 found widespread use in the transport 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 aircraft engines 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 four-engined Focke-Wulf 200 S-1 Condor. It covered the distance to New York in 24 hours and 57 minutes on 10 August 1938.
- 725 PS (715 hp, 533 kW)
- 850 PS (838 hp, 625 kW)
- 880 PS (868 hp, 647 kW)
- 960 PS (947 hp, 706 kW)
- 865 PS (853 hp, 636 kW)
- 730 PS (720 hp, 537 kW)
- ENMA Beta B-4 (Spanish license-built version)
- (9E-C29-775) 785 PS (774 hp; 577 kW) (stroke 174.6 mm (6.87 in), displacement 29.85 l (1,822 cu in))
Specifications (BMW 132 Dc)Edit
Data from Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944
- Type: 9-cylinder single-row supercharged air-cooled radial engine
- Bore: 155.6 mm (6.13 in)
- Stroke: 161.9 mm (6.37 in)
- Displacement: 27.72 l (1,691.6 cu in)
- Length: 1,411 mm (55.55 in)
- Diameter: 1,380 mm (54.33 in)
- Dry weight: 525 kg (1,157 lb)
- Valvetrain: Two overhead valves per cylinder
- Supercharger: Single-speed centrifugal-type supercharger rated to 2,600 m (8,530 ft)
- Fuel system: Mona-Hobson carburetor
- Fuel type: 87 octane rating gasoline
- Oil system: pressure system at 6–7.5 bar (600–750 kPa)
- Cooling system: Air-cooled
- Reduction gear: Farman epicyclic gearing, 0.62:1
- Power output:
- 850 PS (838 hp; 625 kW) for takeoff at 2,450 rpm (1 minute) at sea level
- 780 PS (769 hp; 574 kW) at 2,350 rpm (5 minutes) at sea level
- 690 PS (681 hp; 507 kW) at 2,250 rpm (30 minutes) at sea level
- 550 PS (542 hp; 405 kW) at 2,100 rpm (max. duration) at sea level
- 500 PS (493 hp; 368 kW) at 2,000 rpm (max range) at sea level
- Specific power: 28.15 PS/l (0.45 hp/cu in; 20.70 kW/l)
- Compression ratio: 6.5:1
- Specific fuel consumption: 0.24 kg/PS/h (0.536 lb/hp/h; 0.326 kg/kW/h) at 2,100 rpm
- Oil consumption: 0.003–0.007 kg/PS/h (0.007–0.016 lb/hp/h; 0.004–0.010 kg/kW/h) at 2,100 rpm
- Power-to-weight ratio: 1.49 PS/kg (0.67 hp/lb; 1.10 kW/kg)
- B.M.E.P.=9.75 bar (141.4 psi)
- Wilkinson, Paul H. (1960). Aircraft engines of the World 1960/61 (16th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 260.
- Schneider, Helmut (Dipl.Ing.) (1944). Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944 (in German) (Facsimile reprint 1986 ed.). Leipzig: Herm. Beyer Verlag. p. 369. ISBN 381120484X.
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