Rolls-Royce RB401: Difference between revisions
m →top: Format bare URL, add nationality and wikilink, move ref after punctuation |
|||
| Line 20: | Line 20: | ||
|} |
|} |
||
The '''Rolls-Royce RB.401''' was a two-spool business jet engine which [[Rolls-Royce Limited|Rolls-Royce]] started to develop in the mid-1970s |
The '''Rolls-Royce RB.401''' was a British two-spool [[business jet]] engine which [[Rolls-Royce Limited|Rolls-Royce]] started to develop in the mid-1970s as a replacement for the [[Armstrong Siddeley Viper|Viper]].<ref>Gunston 1989, p.155.</ref><ref>[http://www.flightglobal.com/pdfarchive/view/1979/1979%20-%202715.html ''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== |
==Design and development== |
||
Revision as of 16:10, 12 December 2020
| RB.401 | |
|---|---|
| |
| Rolls-Royce RB.401 turbofan engine at the Rolls-Royce Heritage Trust, Derby | |
| Type | Turbofan |
| Manufacturer | Rolls-Royce |
| First run | 21 December Template:Avyear |
The Rolls-Royce RB.401 was a British two-spool business jet engine which Rolls-Royce started to develop in the mid-1970s as a replacement for the Viper.[1][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)
Data from Jane's.[3]
General characteristics
- Type: High-bypass two-spool turbofan
- Length: 6.8 in (1,545 mm)
- Diameter: 32.4 in (823 mm) (fan casing)
- Dry weight: 985 lb (447 kg)
Components
- Compressor: Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes
- Combustors: Annular
- Turbine: Two-stage LP, single-stage HP with air-cooled blades
- Fuel type: Hydromechanical with provision for electronic monitoring
- Oil system: Self-contained (tank, pumps,filters and cooler)
Performance
- Maximum thrust: Take-off thrust: 5,540 lbf (27.7 kN)
- Overall pressure ratio: 11.5:1 (HP compressor)
- Bypass ratio: 4.2:1
- Air mass flow: 182 lb/s (82.5 kg)
- Thrust-to-weight ratio: 5.6:1
See also
Related lists
References
Notes
- ^ Gunston 1989, p.155.
- ^ Flight, 1979. www.flightglobal.com
- ^ Taylor 1984, p.852
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Taylor, John W.R. Jane's All the World's Aircraft 1984-85., London, Jane's Publishing Company Ltd, 1984. ISBN 0 7106-0801-2.