Armstrong_Siddeley_Python Knowpia

Python
	An Armstrong Siddeley Python during NACA wind tunnel testing in 1949
Type	Turboprop
National origin	United Kingdom
Manufacturer	Armstrong Siddeley
First run	April 1945
Major applications	Westland Wyvern
Developed from	Armstrong Siddeley ASX

The Armstrong Siddeley Python was an early British turboprop engine designed and built by the Armstrong Siddeley company in the mid-1940s. Its main use was in the Westland Wyvern, a carrier-based heavy fighter. The prototypes had used the Rolls-Royce Eagle piston engine, but Pythons were used in production aircraft. In this application, the Python was rated at 4,110 equivalent shaft horsepower (eshp).

Design and development edit

The design started as an experimental pure-turbojet known as the ASX, which commenced testing in 1943. By this point other engine designs were already entering pre-production, and it seemed there was little need for the ASX in its existing form. The design was then modified by the addition of a reduction gearbox to drive a propeller. The turboprop thus formed was named ASP.^[1]

Flight testing edit

Early flight-testing of the Python was carried out using the Lancaster B.1 (FE) TW911 and the Lincoln B.2 RE339/G: in each aircraft Pythons replaced the two outboard Rolls-Royce Merlins.

Lincoln B.2 RF403 had two Pythons similarly installed and was used for high-altitude bombing trials at Woomera, South Australia. These trials were principally of the ballistic casings for the Blue Danube atomic weapon: the Lincoln was the only available aircraft that could accommodate the large weapon casing, measuring 62 inches diameter x 24 feet (7.3 m) in length. The Pythons were fitted to increase the height from which tests could be carried out. Maximum release height and speed for the first eleven tests was 275 mph and 34,783 ft (10,602 m) with a bombing error of 61 ft.^[2]

Python Engine on public display edit

An Armstrong Siddeley Python is on display at the East Midlands Aeropark Castle Donington.

Variants edit

ASP.1 (Python 1): reduction gear ratio 0.127:1
ASP.2 (Python 2): reduction gear ratio 0.135:1
ASP.3 (Python 3)

Applications edit

Avro Lancaster - (test only)
Avro Lincoln - (test only)
Westland Wyvern

Specifications (ASP.3) edit

Data from Flight.^[3]

General characteristics

Type: Turboprop
Length: 123.2 in (313 cm)
Diameter: 54 in (137 cm)
Dry weight: 3,450 lb (1,565 kg)

Components

Compressor: Axial flow; 14 stages
Combustors: 11 combustion chambers
Turbine: Axial flow; two stages

Performance

Maximum power output: 4,110 eshp (3,065 kW) at sea level at 8,000 rpm, including 1,180 lbf (535 kp) exhaust thrust
Overall pressure ratio: 5.35:1
Air mass flow: 52.5 lb/s (23.8 kg/s)
Specific fuel consumption: 0.805 lb/(h eshp)
Power-to-weight ratio: 1.2:1

References edit

Notes edit

^ Gunston 1998, p.19.
^ The National Archives, London, file ES 1/44 E4C Appendix 3 page 1.
^ Flight Global Archive - 1954 www.flightglobal.com. Retrieved: 3 November 2008

Bibliography edit

Gunston, Bill (1998). World encyclopaedia of aero engines : all major aircraft power plants, from the Wright brothers to the present day (4th ed.). Sparkford, Nr Yeovil, Somerset, [England]: P. Stephens. ISBN 978-1852605971.
Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. ISBN 978-1-85260-163-8.
Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. pp. 4d–5d.