Rolls-Royce RB401

You must add a |reason= parameter to this Cleanup template – replace it with {{Cleanup|January 2007|reason=<Fill reason here>}}, or remove the Cleanup template.

The RB401 was a business jet engine which Rolls-Royce started to develop in the mid-1970s.

RB401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB401-07 was taken.

Although the basic configurations of both engines were almost identical, the -07 variant had a larger fan diameter. A single stage fan, driven by 2 stage LP turbine, supercharged an 8 stage HP compressor, driven by a single stage transonic HP turbine. The combustor was annular and the co-annular exhaust featured a lightweight target type thrust reverser.

Leading particulars for -07 variant were as follows:

Fan Diameter: 32.4 in

Take-off Thrust: 5,540 lbf, flat-rated to ISA+15C

Cruise Thrust: 1128lbf (Mach 0.7, 40,000 ft, ISA+10C)

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

This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.

This article about aircraft engines is a stub. You can help Wikipedia by expanding it.