STAL Dovern

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. 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.

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. Jane's 1955-56

General characteristics

Type: Turbojet

Length: 1,095 mm (43.11 in)

Diameter: 3,850 mm (151.57 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