Rolls-Royce RB401

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. 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.

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)

General characteristics

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

Components

• Compressor:

Performance

• Maximum thrust: Take-off Thrust(Sea Level Static): 5,540 lbf, flat-rated to ISA+15C
• Overall pressure ratio: ~20:1
• Power-to-weight ratio:

See also

Related lists

• List of aircraft engines
  

References

Bibliography

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