Armstrong Siddeley Mamba
| Mamba | |
|---|---|
 |
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| ASM.3 engine at the Armstrong and Aircraft Museum at Bamburgh Castle. | |
| Type | Gas turbine turboprop |
| National origin | United Kingdom |
| Manufacturer | Armstrong Siddeley |
| First run | April 1946 |
| Major applications | Boulton Paul Balliol A.W. Apollo Short Seamew |
| Developed into | Double Mamba Adder |
The Mamba was a British turboprop engine produced by Armstrong Siddeley in the late 1940s and 1950s, producing around 1,500 effective horsepower (1,100 kW).
Contents |
[edit] Design and development
The Mamba was a compact engine [1] 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 company internal designation was ASM (Armstrong Siddeley Mamba). The ASM.3 gave 1,475 ehp and the ASM.6 was rated at 1,770 ehp. A 500-hour test was undertaken in 1948.[1] The Mamba was the first turboprop engine to power the Douglas DC-3. In 1949, a Dakota testbed was converted to take two Mambas.
The Mamba was developed into the form of the Double Mamba, which was used on the Fairey Gannet anti-submarine aircraft for the Royal Navy. This was essentially two Mambas lying side-by-side and driving contra-rotating propellers through a common gearbox. A turbojet version of the Mamba was developed as the Armstrong Siddeley Adder, by removing the reduction gearbox.[2]
[edit] Variants and applications
- ASM.3
- Armstrong Whitworth Apollo
- Avro Athena
- Boulton Paul Balliol
- Breguet Vultur
- Miles M.69 Marathon II
- Douglas C-47 Dakota
- ASM.6
- Swiss-Mamba SM-1 (turbofan variant)
[edit] Engines on display
An Armstrong Siddeley Mamba is on static display at the Midland Air Museum, Coventry Airport, Warwickshire and at the Royal Air Force Museum Cosford.
[edit] Specifications (ASM.3)
Data from Flight[3]
General characteristics
- Type: Turboprop
- Length: 87.3 in (2217.4 mm)
- Diameter: 29 in (737 mm)
- Dry weight: 780 lb (354 kg)
Components
- Compressor: 10 stage axial flow
- Combustors: 6 combustion chambers
- Turbine: 2 stage
Performance
- Maximum power output: 1,320 shp plus 405 lbf (1.80 kN) thrust (1,475 eshp)
- Overall pressure ratio: 5.35:1
- Specific fuel consumption: 0.8 lb/h/eshp
- Power-to-weight ratio: 1.9 eshp/lb
[edit] See also
- Related lists
[edit] References
[edit] Notes
- ^ a b "Aero Engine Information". RAF Museum. http://www.rafmuseum.org.uk/cosford/collections/engines/engine_info.cfm?engine_id=6. Retrieved 2008-06-06.
- ^ Gunston 1989, p.20.
- ^ Flight Global Archive - 1954 www.flightglobal.com. Retrieved: 4 November 2008
[edit] Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
[edit] External links
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