Rolls-Royce RB401
| RB.401 | |
|---|---|
| Type | Turbofan |
| Manufacturer | Rolls-Royce |
| First run | Template:Avyear |
The Rolls-Royce RB.401 was a business jet engine which Rolls-Royce started to develop in the mid-1970s.[1] 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.
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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