Rolls-Royce RB401
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The Rolls-Royce RB.401 was a British two-spool
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engine which Rolls-Royce started to develop in the mid-1970s as a replacement for the
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.''Flight'', 1979. www.flightglobal.com
/ref> 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)


See also


References


Notes


Bibliography

* Gunston, Bill. ''World Encyclopedia of Aero Engines''. Cambridge, England. Patrick Stephens Limited, 1989. * Taylor, John W.R. ''Jane's All the World's Aircraft 1984-85.'', London, Jane's Publishing Company Ltd, 1984. . {{Rolls-Royce plc aeroengines RB401 High-bypass turbofan engines 1970s turbofan engines