Rolls-Royce RB401: Difference between revisions
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|caption= Rolls-Royce RB.401 turbofan engine at the [[Rolls-Royce Heritage Trust, Derby]] |
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==References== |
==References== |
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===Notes=== |
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Revision as of 14:33, 17 August 2019
| RB.401 | |
|---|---|
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| Rolls-Royce RB.401 turbofan engine at the Rolls-Royce Heritage Trust, Derby | |
| Type | Turbofan |
| Manufacturer | Rolls-Royce |
| First run | Template:Avyear |
The Rolls-Royce RB.401 was a two-spool business jet engine which Rolls-Royce started to develop in the mid-1970s[1] as a replacement for the Viper.[2] 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
See also
Related lists
References
Notes
- ^ Gunston 1989, p.155.
- ^ http://www.flightglobal.com/pdfarchive/view/1979/1979%20-%202715.html
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9