Armstrong Siddeley Double Mamba
| Double Mamba | |
|---|---|
| |
| Preserved Double Mamba at the Imperial War Museum Duxford | |
| Type | Turboprop |
| Manufacturer | Armstrong Siddeley |
| First run | 29 September 1949 (First flight) |
| Major applications | Fairey Gannet |
| Developed from | Armstrong Siddeley Mamba |
The Armstrong Siddeley Double Mamba is a turboprop engine design developed in the late 1940s of around 3,000–4,000 hp (2,200–3,000 kW). It was used mostly on the Fairey Gannet anti-submarine aircraft developed for the Fleet Air Arm of the Royal Navy.
Design and development
[edit]The Double Mamba (rarely known as the Twin Mamba) was a development of the Armstrong Siddeley Mamba with two Mambas driving contra-rotating propellers through a combining gearbox.[1]
Engine starting was by cartridge; however, forced air restart was achieved in flight. One engine could be shut down in flight to conserve fuel. Shutting down one engine also stopped one of the propellers.
Variants
[edit]
- ASMD.1
- 2,950 shp (2,200 kW) (2 x ASMa.3) used on Fairey Gannet A.S. Mk.1 and Blackburn B-88
- ASMD.3
- 3,145 shp (2,345 kW) (2 x ASMa.5) used on Fairey Gannet A.S. Mk.4
- ASMD.4
- 3,875 hp (2,890 kW) (2 x ASMa.6) used on Fairey Gannet AEW Mk.3
- ASMD.8
- 3,875 hp (2,890 kW) (2 x ASMa.6) used on Fairey Gannet AEW Mk.3
Applications
[edit]The Double Mamba engine was also proposed for the Westland Westminster, a 30-seat helicopter that was later built as a prototype powered by a pair of Napier Eland E220 turboshaft engines.
Engines on display
[edit] |
Preserved Double Mamba engines are on public display at the:
- Australian National Aviation Museum
- Deutsches Museum Flugwerft Schleissheim
- Gatwick Aviation Museum
- South Yorkshire Aircraft Museum
- Imperial War Museum Duxford
- Midland Air Museum
- Queensland Air Museum
- East Midlands Aeropark
- Museum of Berkshire Aviation
Specifications (ASMD.3)
[edit]
Data from Flight[2]
General characteristics
- Type: Turboprop engine
- Length: 102.25 in (2,597 mm)
- Diameter: 52.8 in (1,341 mm)
- Dry weight: 2,170 lb (984 kg)
Components
- Compressor: 10 stage axial (x2)
- Combustors: Six combustion chambers (x2)
Performance
- Maximum power output: 2,960 eshp (2,207 kW)
- Overall pressure ratio: 5.35:1
- Air mass flow: 18.5 lb/sec (8.4 kg/s) per single Mamba unit
- Specific fuel consumption: 1.71 lb/(lbf·h)
- Power-to-weight ratio: 1.36 eshp/lb
See also
[edit]Related development
Comparable engines
Related lists
References
[edit]Notes
[edit]- ^ Gunston 1989, p.20.
- ^ Aero Engines 1954 Flight International magazine, Flight Global/Archives, 9 April 1954, on www.flightglobal.com. Retrieved: 29 October 2016
Bibliography
[edit]- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
[edit]