Siemens-Halske Sh 22

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Sh 22
Type	Radial engine
National origin	Germany
Manufacturer	Siemens-Halske
First run	1930
Developed from	Siemens-Halske Sh.21
Developed into	Bramo 323

The Siemens-Halske Sh 22 (also known as SAM 22) was a nine-cylinder aircraft radial engine manufactured by Siemens & Halske in Germany in the 1930s. Following the reorganization of its manufacturer and change in military nomenclature, the engine became known as the Bramo 322.

It was a result of a series of modifications to the original Bristol Jupiter IV design, which Siemens licensed in 1929. The first modifications were to "Germanize" the dimensions, producing the Sh.20 and Sh.21. The design was then bored out to produce the 950 hp (708 kW) Sh.22 in 1930. Like the Jupiter, the Sh.22 featured a rather "old" looking arrangement with rather prominent valve pushrods on the front of the engine. In the mid-1930s the Reich Air Ministry (RLM) rationalized engine naming, and Bramo was given the 300-block of numbers, the Sh.14 and Sh.22 becoming the Bramo 314 and 322 respectively. The 322 never matured and remained unreliable. It became a base for the more successful Bramo 323.

Applications

Specifications (Bramo 322H-2)

Data from Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv,^[1] Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944^[2]

General characteristics

Type: 9-cylinder single-row supercharged air-cooled radial engine
Bore: 154 mm (6.06 in)
Stroke: 160 mm (6.30 in)
Displacement: 26.82 L (1,636.8 in³)
Length: 1,285 mm (50.59 in)
Diameter: 1,324 mm (52.13 in)
Dry weight: 490 kg (1,080 lb) dry, unequipped

506 kg (1,116 lb) wet, equipped

Components

Valvetrain: Two overhead valves per cylinder driven by pushrods and rockers
Supercharger: Single-speed centrifugal type supercharger running at 6.25:1
Fuel system: Carburetor
Fuel type: 87 octane gasoline
Oil system: pressure fed at 6–8 bar (87–116 psi)
Cooling system: Air-cooled
Reduction gear: Farman epicyclic gearing, 0.62:1

Performance

Power output:

650 PS (641 hp; 478 kW) at 2,150 rpm (5 minutes) at sea level
585 PS (577 hp; 430 kW) at 2,080 rpm (30 minutes) at sea level
520 PS (513 hp; 382 kW) at 2,000 rpm (max. continuous / cruise) at sea level

Specific power: 24.21 PS/L (0.39 hp/cu in; 17.81 kW/L)
Compression ratio: 6.4:1
Specific fuel consumption: 0.255 kg/PSh (0.570 lb/(hp⋅h); 0.347 kg/kWh) at max continuous
Oil consumption: 0.005–0.015 kg/PSh (0.011–0.034 lb/(hp⋅h); 0.007–0.020 kg/kWh) at max continuous
Power-to-weight ratio: 1.333 PS/kg (0.596 hp/lb; 0.980 kW/kg) at cruise
B.M.E.P.: 9.1 atm (9.2 bar; 134 psi)

References

^ Tsygulev (1939). Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv (Авиационные моторы военных воздушных сил иностранных государств) (in Russian). Moscow: Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR. Archived from the original on 2009-03-24.
^ 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. 377. ISBN 381120484X.

v t e Siemens-Halske aircraft engines
Rotary engines	Sh I Sh II Sh III
Radial engines	Sh 4 Sh 5 Sh 6 Sh 7 Sh 11 Sh 12 Sh 13 Sh 14 Sh 15 Sh 22

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