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.

RB.401
Rolls-Royce RB.401 turbofan engine at the Rolls-Royce Heritage Trust, Derby
Type	Turbofan
Manufacturer	Rolls-Royce
First run	21 December 1975

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

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)

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

• Maximum thrust: Take-off thrust: 5,540 lbf (24.7 kN)
• Overall pressure ratio: 11.5:1 (HP compressor)
• Bypass ratio: 4.2:1
• Air mass flow: 182 lb/s (82.5 kg)
• Thrust-to-weight ratio: 5.6:1

See also

Related lists

• List of aircraft engines

References

Wikimedia Commons has media related to Rolls-Royce RB401.

Notes

Bibliography