Armstrong Siddeley Mamba
| Mamba | |
|---|---|
 | |
| ASM.3 engine at the Armstrong and Aircraft Museum at Bamburgh Castle. | |
| Type | Turboprop |
| National origin | United Kingdom |
| Manufacturer | Armstrong Siddeley |
| First run | April 1946 |
| Major applications | Boulton Paul Balliol A.W. Apollo Short Seamew |
| Developed into | Armstrong Siddeley Double Mamba Armstrong Siddeley Adder |
The Armstrong Siddeley 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).
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 Ministry of Supply 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] 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.
A turbojet version of the Mamba was developed as the Armstrong Siddeley Adder, by removing the reduction gearbox.[2]
Variants and applications
- ASM.3 Mamba[3]
- Armstrong Whitworth Apollo
- Avro Athena
- Boulton Paul Balliol
- Breguet Vultur
- Miles M.69 Marathon II
- Douglas C-47 Dakota
- ASM.5
- [3]
- ASM.6 Mamba[3]
- Short Seamew
- ASM.7
- A version for civil applications[3]
- Swiss-Mamba SM-1 (aft turbofan variant)
- EFW N-20
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.
A Mamba is also on display at the Aviation Heritage Museum (Western Australia).[4]
Specifications (ASM.3)
Data from Flight[5]
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
- Air mass flow: 18.5 lb/s (8.4 kg/s)
- Specific fuel consumption: 0.8 lb/h/eshp
- Power-to-weight ratio: 1.9 eshp/lb
See also
- Related development
- Related lists
References
Notes
- 1 2 "Aero Engine Information". RAF Museum. Retrieved 2008-06-06.
- ↑ Gunston 1989, p.20.
- 1 2 3 4 Taylor, John W.R. FRHistS. ARAeS (1955). Jane's All the World's Aircraft 1955-56. London: Sampson, Low, Marston & Co Ltd.
- ↑ http://www.raafawa.org.au/museum/engines
- ↑ "Aero Engines 1954", Flight (www.flightglobal.com), 9 April 1954, p. 446, retrieved 4 November 2008
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
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Wikimedia Commons has media related to Armstrong Siddeley Mamba. |
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