STAL Dovern
The STAL Dovern was a Swedish turbojet design of the early 1950s, named after a lake in Finspång municipality in Östergötland, Sweden.[1] Intended to power the Saab 35 Draken, this aircraft was powered by the Rolls-Royce Avon instead. The Dovern did not enter production.
| Dovern | |
|---|---|
 | |
| Type | Turbojet |
| Manufacturer | Svenska Turbinfabriks AB Ljungström |
| First run | 1951 |
| Major applications | Saab 35 Draken (intended) |
Design and development
The STAL company had been designing gas turbine engines since 1935. Their first running engine was the Skuten, ground tested in 1949 but not flown.[2] The Dovern was the next design, featuring a nine-stage axial compressor and single-stage turbine. First run in 1951, the engine was flight tested during 1953 using an Avro Lancaster provided by Air Service Training. The engine was installed underneath in a nacelle faired-in to the Lancaster's bomb bay. After several thousand hours of ground running and more than 300 hours of flight testing the engine was not selected, the Rolls-Royce Avon being preferred.[3]
Applications
- Avro Lancaster (test bed only)
- Saab 35 Draken (intended application)
Variants
- Dovern
- Base variant.
- Dovern IIA
- Basic engine without de-icing
- Dovern IIB
- Compressor bleed air system added for ice protection.
- Dovern IIC
- Afterburning version producing 45 kN (10,200 lbf) thrust.
Specifications (Dovern IIB)
Data from Flight.[4] Jane's 1955-56[2]
General characteristics
- Type: Turbojet
- Length: 3,850 mm (151.57 in)
- Diameter: 1,095 mm (43.11 in)
- Dry weight: 1,220 kg (2,690 lb) dry
Components
- Compressor: Nine-stage axial flow
- Combustors: Nine combustion chambers
- Turbine: Single-stage
- Fuel type: Aviation kerosene to D.Eng R.D. 2482
- Oil system: Dry sump with gear pressure and scavenge pumps at 240–310 kilopascals (35–45 psi)
Performance
- Maximum thrust: 32.29 kN (7,260 lbf) at 7,200 rpm at sea level for take-off
- Overall pressure ratio: 5.2:1
- Air mass flow: 54.9 kg (121 lb) / s
- Turbine inlet temperature: 870 °C (1,140 K; 1,600 °F)
- Specific fuel consumption: 0.009 kg/(kN h) (0.92 lb/(lbf h)
- Thrust-to-weight ratio: 2.76:1
References
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Wikimedia Commons has media related to STAL Dovern. |
- Notes
- "Sjöareal och sjöhöjd" (.pdf) (in Swedish). Swedish Meteorological and Hydrological Institute. Retrieved 12 April 2014.
- Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd.
- Gunston 1989, p. 165.
- Aero engines 1954 - Flight - 9 April 1954, p. 467 Retrieved: 6 June 2012
- Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Kay, Anthony L. (2007). Turbojet History and Development 1930-1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary (1st ed.). Ramsbury: The Crowood Press. ISBN 978-1861269393.