Armstrong Siddeley Mamba
|Mamba engine on display at Sheffield Hallam University|
|National origin||United Kingdom|
|First run||April 1946|
|Major applications||Boulton Paul Balliol|
|Developed into||Armstrong Siddeley Double Mamba|
Armstrong Siddeley Adder
Armstrong Siddeley gas turbine engines were named after snakes.
Design and development
The Mamba was a compact engine with a 10-stage axial compressor, six combustion chambers and a two-stage power turbine. The epicyclic reduction gearbox was incorporated in the propeller spinner. Engine starting was by cartridge. The Ministry of Supply designation was ASMa (Armstrong Siddeley Mamba). The ASMa.3 gave 1,475 ehp and the ASMa.6 was rated at 1,770 ehp. A 500-hour test was undertaken in 1948 and the Mamba was the first turboprop engine to power the Douglas DC-3, when in 1949, a Dakota testbed was converted to take two Mambas.
The Mamba was also developed into the form of the Double Mamba, which was used to power the Fairey Gannet anti-submarine aircraft for the Royal Navy. This was essentially two Mambas lying side-by-side and driving contra-rotating propellers separately through a common gearbox.
Variants and applications
- ASMa.3 Mamba
- Armstrong Whitworth Apollo
- Avro Athena
- Boulton Paul Balliol
- Breguet Vultur
- Miles M.69 Marathon II
- Douglas C-47 Dakota
- ASMa.5 Mamba
- Development engine for Armstrong Siddeley ASMD.3 Double Mamba
- ASMa.6 Mamba
- Short Seamew
- ASMa.7 Mamba
- A version for civil applications
- Swiss-Mamba SM-1 (aft turbofan variant)
- EFW N-20
- Mamba 112
Engines on display
A Mamba is also on display at the Aviation Heritage Museum (Western Australia).
A Swiss-Mamba SM-1 is on display at the Flieger-Flab-Museum Dübendorf.
A Mamba is also on display at the Hertha Ayrton STEM Centre, Sheffield Hallam University, UK.
- Type: Turboprop
- Length: 90.2 in (2,290 mm)
- Diameter: 33 in (840 mm)
- Frontal area: 5.9 sq ft (0.55 m2)
- Dry weight: 850 lb (390 kg)
- Compressor: 11 stage axial flow
- Combustors: Annular combustion chamber with 24 vapourising burners
- Turbine: 3 stage axial flow
- Fuel type: Aviation Kerosene / JP-4
- Maximum power output: 1,650 shp (1,230 kW) plus 320 lbf (1.4 kN) thrust ; 1,770 shp (1,320 kW) (equivalent) at 15,000 rpm
- Overall pressure ratio: 6:1
- Air mass flow: 21.5 lb/s (9.8 kg/s) at 15,000 rpm
- Specific fuel consumption: 0.69 lb/shp/h (0.42 kg/kW/h) (equivalent shaft horsepower)
- Power-to-weight ratio: 2.08 shp/lb (3.42 kW/kg) (equivalent shaft horsepower)
- "Aero Engine Information". RAF Museum. Archived from the original on 16 November 2007. Retrieved 6 June 2008.
- Gunston 1989, p.20.
- Taylor, John W.R. FRHistS. ARAeS (1955). Jane's All the World's Aircraft 1955-56. London: Sampson, Low, Marston & Co Ltd.
- Studio, Cicada. "Armstrong Siddeley Mamba". www.raafawa.org.au. Retrieved 16 March 2019.
- Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 122–123.
|Wikimedia Commons has media related to Armstrong Siddeley Mamba.|