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Rolls-Royce RB401

1970s British turbofan aircraft engine From Wikipedia, the free encyclopedia

Rolls-Royce RB401
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The Rolls-Royce RB.401 was a British two-spool business jet engine which Rolls-Royce started to develop in the mid-1970s as a replacement for the Viper.[1][2] RB.401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB.401-07 was taken.

Quick facts RB.401, Type ...

Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled.

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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.

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Specifications (RB.401-07)

Data from Jane's.[3]

General characteristics

  • Type: High-bypass two-spool turbofan
  • Length: 60.8 in (1,545 mm)
  • Diameter: 32.4 in (823 mm) (fan casing)
  • Dry weight: 985 lb (447 kg)

Components

  • Compressor: Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes
  • Combustors: Annular
  • Turbine: Two-stage LP, single-stage HP with air-cooled blades
  • Fuel type: Hydromechanical with provision for electronic monitoring
  • Oil system: Self-contained (tank, pumps,filters and cooler)

Performance

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See also

Related lists

References

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