Rolls-Royce/MAN Turbo RB193

RB.193
Rotating nozzle detail of the RB.193
Type Vectored thrust turbofan
Manufacturer Rolls-Royce Limited/MAN Turbo/Bristol Siddeley
First run December 1967
Major applications VFW VAK 191B
Program cost £8,000,000 (1966)

The Rolls-Royce/MAN Turbo RB.193 is a vectored thrust turbofan engine designed and manufactured by Rolls-Royce and MAN Turbo in the mid-1960s. The engine test flew in its sole application, the VFW VAK 191B VTOL fighter aircraft but production did not follow after cancellation of the associated aircraft project.

Design and development

The RB.193 was a joint development project by Rolls-Royce/MAN Turbo originally designed to meet a requirement for the VFW VAK 191B project, design work commenced after a contract from the Federal German Ministry of Defence was signed in December 1965. Bristol Siddeley (from 1966 part of Rolls-Royce) were sub-contracted to manufacture components for the engine.[1]

The design was similar in concept and closely related to the earlier Bristol Siddeley Pegasus, employing the same layout of 'hot' and 'cold' pairs of rotating thrust nozzles, internal airflow was the same as the Spey. The engine first ran at Derby in December 1967 with flight testing of the VFW VAK 191B commencing in 1971 with the first free hovering flight taking place at Bremen on 10 September. The aircraft later successfully transitioned from hovering to forward flight at Manching in October 1972.[2][3] By the end of the test programme in 1975 the RB.193 had accumulated 12 hours of flight time and 91 flights.[4]

Applications

Engines on display

A VFW VAK 191B aircraft fitted with an RB.193-12 is on display at the Deutsches Museum Flugwerft Schleissheim, panels have been removed to allow viewing of the rotating nozzle and mechanisms.

Specifications (RB.193-12)

Data from Gunston and Jane's.[5][6]

General characteristics

  • Type: High bypass twin-spool vectored thrust turbofan
  • Length: 101.4 in (257.5 cm)
  • Diameter: 34.3 in (84.5 mm) (Internal fan diameter)
  • Dry weight: 1,742 lb (790 kg) Installed weight 2,315 lb (1,050 kg)

Components

  • Compressor: Axial compressor, Three-stage fan/LP, two-stage IP, counter-rotating six-stage HP
  • Combustors: Annular
  • Turbine: Three-stage LP, single-stage HP (counter-rotating)

Performance

See also

Related development

Comparable engines

Related lists

References

Notes
  1. ↑ Flightglobal archive - Flight, January 1966 Retrieved: 21 July 2009
  2. ↑ Flightglobal archive - Flight, January 1969 Retrieved: 27 October 2014
  3. ↑ - 0273.html Flightglobal archive - Flight, February 1972 Archived 5 November 2012 at the Wayback Machine. Retrieved: 27 October 2014
  4. ↑ EADS - VFW VAK 191B history Retrieved: 21 July 2009.
  5. ↑ Gunston 1989, p.153.
  6. ↑ Taylor 1972, p.674.
Bibliography

  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • Taylor, John W.R. Jane's All the World's Aircraft 1972-73., London, Sampson Low, Marston and Company Ltd, 1972. ISBN 978-0354001090.
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