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Rolls-Royce RB401: Wikis

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RB.401
Type Turbofan
Manufacturer Rolls-Royce
First run 1975

The Rolls-Royce RB.401 was a business jet engine which Rolls-Royce started to develop in the mid-1970s.[1] RB.401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB.401-07 was taken. Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled.

Contents

Design and development

Although the basic configuration of both engines was almost identical, the -07 variant had a larger fan diameter. The -06 version HP compressor was based on the eight-stage version of the RC34B research compressor, unscaled, whereas the -07 was a scaled-up unit. A single stage fan, driven by a two-stage LP turbine, supercharged the HP compressor which was driven by the single stage transonic HP turbine. The combustor was annular and the co-annular exhaust featured a lightweight target type thrust reverser.

Specifications (RB.401-07)

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General characteristics

  • Type: High bypass Turbofan
  • Length:
  • Diameter: 32.4 in (fan)
  • Dry weight:

Components

  • Compressor:

Performance

See also

Related lists

References

Notes

  1. ^ Gunston 1989, p.155.

Bibliography

  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

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