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
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 (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
- overhead valvesper cylinder driven by pushrods and rockers
- centrifugal type superchargerrunning 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.
- ISBN 381120484X.