Siemens-Halske Sh 22
| 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
- Dornier Do 19 (proposed)
- Fieseler Fi 98
- Heinkel He 46
- Henschel Hs 122
- Junkers W 34
- Junkers Ju 86ab1 prototype
Specifications (SAM 22B)
Data from [1]
General characteristics
- Type: Nine-cylinder single-row supercharged air-cooled radial engine
- Bore: 154 mm (6.06 in)
- Stroke: 160 mm (6.3 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: 465 kg (1,025 lb)
Components
- Valvetrain: Two overhead valves per cylinder
- Supercharger: Single-speed centrifugal type supercharger
- Fuel system: Carburetor
- Fuel type: 80 octane rating gasoline
- Cooling system: Air-cooled
- Reduction gear: Farman epicyclic gearing, 1.6:1
Performance
- Power output: 442 kW (592 hp) at 2,100 rpm for takeoff
- Specific power: 16.49 kW/l (0.36 hp/in³)
- Compression ratio: 5.2:1
- Power-to-weight ratio: 0.95 kW/kg (0.58 hp/lb)
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.
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