Armstrong Siddeley Viper

From Wikipedia, the free encyclopedia
Jump to navigation Jump to search

Viper
Rolls-Royce Viper 1.jpg
Preserved Rolls-Royce Viper turbojet
Type Turbojet
Manufacturer Armstrong Siddeley
Rolls-Royce Limited
First run April 1951
Major applications BAC Jet Provost
HS Dominie
Aermacchi MB-326
Developed from Armstrong Siddeley Adder

The Armstrong Siddeley 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[edit]

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 originally developed as an expendable engine for production versions of the Jindivik target drone. Like the J85, the limited-life components and total-loss oil systems were replaced with standard systems for use in manned aircraft.[2]

Because it was initially developed as an expendable engine, the Viper was subject to many recurring maintenance issues. This led to the development of the first Power by the Hour program in which operators would pay a fixed hourly rate to Bristol Siddeley for the continual maintenance of the engines.[3]

Variants[edit]

Rolls-Royce Viper in RAF Museum Cosford

Data from:Jane's All the World's Aircraft 1955-56[4], Jane's all the World's Aircraft 1959-60[5], Jane's All the World's Aircraft 1962-63[6]

ASV.1
Short life design study; 1,145 lbf (5.09 kN).
ASV.2
Developed short life version, first run in April 1951; 1,145 lbf (5.09 kN).
ASV.3
(Mk.100) Short life for missile/target applications, flight-tested in the tail of an Avro Lancaster November 1952; 1,640 lbf (7.30 kN).
ASV.4
Short life for missile/target applications first run in 1952, 1,750 lbf (7.78 kN).
ASV.5
(Mk. 101) Extended life version for manned aircraft.[4]
ASV.6
Short life for missile/target applications; 1,900 lbf (8.45 kN).
ASV.7
ASV.7/R
ASV.7 with re-heat;2,470 lbf (10.99 kN).
ASV.8
(became Viper 8 and Mk.102); Long-life version rated at 1,750 lbf (7.78 kN) for Jet Provost T Mk.3.
ASV.9
(became Viper 9 and Mk.103) Similar to ASV.8 with improved turbine materials; 2,000 lbf (8.90 kN).
ASV.10
Long-life version with re-designed Sapphire-style compressor first run in January 1956; 1,900 lbf (8.45 kN).
ASV.11
(became Viper 11 and Mk.200) ASV.10 with increased mass-flow; 2,500 lbf (11.12 kN).
ASV.12
(became Viper 12) up-rated ASV.11 with higher JPT and rated at 2,700 lbf (12.01 kN)
Viper 8
(Mk.102 / Mk.104): Engines for the Hunting-Percival Jet Provost TMk.3 (Mk.102) and GAF Jindivik Mk.102B target drone (Mk.104).
Viper 9
(Mk.103): Powered the Bell X-14 and Handley Page HP 115 among others.
Viper 11
(Mk.200): Powered the Hunting-Percival Jet Provost TMk.4(Mk202) and GAF Jindivik Mk.3 among others.
Viper 12
see ASV.12 above
Viper 20
(Mk.500 series): Powered the Hawker Siddeley HS.125 and Piaggio-Douglas PD.808 among others.
Viper 22
Built under licence by Piaggio for the Aermacchi MB.326
Mk.100
see ASV.3 above
Mk.101
see ASV.5 above
Mk.102
see ASV.8 above
Mk.103
see ASV.9 and Viper 9 above
Mk.104
see ASV.12 above
Mk.200
Mk.201
Mk.202
Mk.204

Evidence found on a surviving Mk.204 engine suggests this is a Mk.202 variant with increased temperature and oil pressure transmission capabilities. These are thought to be safety measures installed for use in Jet Provost aircraft used by HRH Prince Charles during his Royal Air Force flight training programme.

Mk.301
Mk.521
Mk.522
Mk.525
Mk.601
Mk.805
de-rated to 4,000 lbf (17.79 kN), powered Fuji T1F1 prototype and T-1A production aircraft, as well as the Hunting H.126 jet-flap research aircraft.
M.D.30 Viper
Engines licence-built and developed by Dassault Aviation[4]

Applications[edit]

Specifications (Viper ASV.12)[edit]

Data from [7]

General characteristics

  • Type: Turbojet
  • Length: 64.0 in (1,625 mm)
  • Diameter: 24.55 in (624 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

oil consumption=1.25 pt/h (0.7 L/h)

See also[edit]

Related development

Comparable engines

Related lists

References[edit]

Notes[edit]

  1. ^ Dominie T1 www.raf.mod.uk. Retrieved: 14 October 2009
  2. ^ Gunston 1989, p.20.
  3. ^ "Selling the DH125". Flight Global.
  4. ^ a b c Taylor, John W.R. FRHistS. ARAeS (1955). Jane's All the World's Aircraft 1955-56. London: Sampson, Low, Marston & Co Ltd.
  5. ^ Bridgman, Leonard, ed. (1959). Jane's all the World's Aircraft 1959-60. London: Sampson Low, Marston & Co. Ltd.
  6. ^ Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
  7. ^ Flight Global Archive - 1955 Retrieved: 3 November 2008

Bibliography[edit]

  • Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

External links[edit]