Armstrong Siddeley Viper
| Viper | |
|---|---|
| |
| Preserved Rolls-Royce Viper Turbojet | |
| Type | Turbojet |
| Manufacturer | Armstrong Siddeley Rolls-Royce Limited |
| First run | April Template:Avyear |
| Major applications | BAC Jet Provost HS Dominie |
| Developed from | AS Adder |
The Viper is a British turbojet engine developed and produced by Armstrong Siddeley and then by its successor companies Bristol Siddeley and Rolls-Royce Limited. It entered service in 1953 and remained in use with the Royal Air Force, powering its Dominie T1 navigation training aircraft until January 2011.[1]
Design and development
The design originally featured a seven-stage compressor based on their Adder engine — the Viper is in effect a large-scale Adder.
Like the similar J85 built in United States, the Viper was developed as an expendable engine for powering production versions of the Jindivik target drone,[2] but, again like the J85, the limited-life materials and total-loss oil systems were replaced with standard systems for use in manned aircraft.
Engines on display
Preserved Viper engines are on public display at the following museums:
- Midland Air Museum
- Royal Air Force Museum Cosford
- Solent Sky
- Aeroventure,South Yorkshire Aircraft Museum
- South African Air Force Museum Port Elizabeth
Applications
- Aermacchi MB-339
- Aermacchi MB-326
- Atlas Aircraft Impala
- Avro Shackleton
- BAC Jet Provost
- BAC Strikemaster
- Bell X-14
- Embraer AT-26 Xavante
- GAF Jindivik
- Hawker Siddeley Dominie
- Handley Page HP.115
- IAR 99
- Piaggio PD.808
- Saunders-Roe SR.53
- Soko J-22 Orao/IAR-93
- Soko G-2 Galeb
- Soko G-4 Super Galeb
Specifications (Viper ASV.12)
Data from [3]
General characteristics
- Type: Turbojet
- Length: 64.0 in (1625 mm)
- Diameter: 24.55 in (966 mm)
- Dry weight: 549 lb (249 kg)
Components
- Compressor: Seven stage axial
- Combustors: Annular, 24 burners
- Turbine: Single stage
- Fuel type: AVTUR, AVTAG
- Oil system: scavenge, metered
Performance
- Maximum thrust: 2,700 lb (1225 kg) at 13,800 rpm
- Overall pressure ratio: 4.3:1
- Air mass flow: 44 lb/sec (20 kg/sec)
- Specific fuel consumption: 1.09 lb/hr/lb
- Thrust-to-weight ratio: 4.9:1
See also
Related development
Comparable engines
Related lists
References
Notes
- ^ Dominie T1 www.raf.mod.uk. Retrieved: 14 October 2009
- ^ Gunston 1989, p.20.
- ^ Flight Global Archive - 1955 Retrieved: 3 November 2008
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
