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Armstrong Siddeley Mamba

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Armstrong Siddeley Mamba

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).

Contents

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 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 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.

Variants and applications

ASM.3 Mamba
Armstrong Whitworth Apollo Avro Athena Boulton Paul Balliol Breguet Vultur Miles M.69 Marathon II Douglas C-47 Dakota
ASM.5
ASM.6 Mamba
Short Seamew
ASM.7
A version for civil applications
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).

Specifications (ASM.3)

Data from Flight

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
  • References

    Armstrong Siddeley Mamba Wikipedia


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