Armstrong Siddeley Double Mamba
| Double Mamba | |
|---|---|
| |
| Preserved Double Mamba at the Imperial War Museum Duxford | |
| Type | Turboprop |
| Manufacturer | Armstrong Siddeley |
| First run | 29 September Template:Avyear (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 (2,500–3,000 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
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.
Variants and applications
The Ministry of Supply designation system for these engines reflects the obvious linkage to their Mamba lineage:
AS = Armstrong Siddeley
M = Mamba
D = Double
num = model
| Model | Thrust (ehp) | Component engines |
Aircraft fitted |
|---|---|---|---|
| ASMD.1 | 2,950 | 2 x ASM.3 | Fairey Gannet A.S. Mk.1 Blackburn B88 (prototype) |
| ASMD.3 | 3,145 | 2 x ASM.5 | Fairey Gannet A.S. Mk.4 |
| ASMD.4 | 3,875 | 2 x ASM.6 | Fairey Gannet AEW Mk.3 |
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
Preserved Double Mamba engines are on public display at the:
- Australian National Aviation Museum
- Caloundra Air Museum
- Deutsches Museum Flugwerft Schleissheim
- Gatwick Aviation Museum
- Imperial War Museum Duxford
- Midland Air Museum
- Gatwick Aviation Museum
Specifications (ASMD.3)
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
Related development
Comparable engines
Related lists
References
Notes
- ^ Gunston 1989, p.20.
- ^ Flight Global Archive -1954 www.flightglobal.com. 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
