Rolls-Royce RB401: Difference between revisions
Content deleted Content added
Add image |
Add source, add specs and cite |
||
| Line 9: | Line 9: | ||
|type=[[Turbofan]] |
|type=[[Turbofan]] |
||
|manufacturer=[[Rolls-Royce Limited|Rolls-Royce]] |
|manufacturer=[[Rolls-Royce Limited|Rolls-Royce]] |
||
|first run= {{avyear|1975}} |
|first run= 21 December {{avyear|1975}} |
||
|major applications= |
|major applications= |
||
|number built = |
|number built = |
||
| Line 29: | Line 29: | ||
<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] --> |
<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] --> |
||
<!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully-formatted line with <li> --> |
<!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully-formatted line with <li> --> |
||
|ref=''Jane's''.<ref>Taylor 1984, p.852</ref> |
|||
|type=High bypass Turbofan |
|||
|type=High-bypass two-spool turbofan |
|||
|length= |
|||
| |
|length=6.8 in (1,545 mm) |
||
|diameter=32.4 in 823 mm (fan casing) |
|||
|weight= |
|||
|weight=985 lb (447 kg) |
|||
|compressor= |
|||
|compressor=Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes |
|||
|combustion= |
|combustion=Annular |
||
|turbine= |
|||
|turbine=Two-stage LP, single-stage HP with air-cooled blades |
|||
|fueltype= |
|||
|fueltype=Hydromechanical with provision for electronic monitoring |
|||
|oilsystem= |
|||
|oilsystem=Self-contained (tank, pumps,filters and cooler) |
|||
|power= |
|power= |
||
|thrust=Take-off Thrust(Sea Level Static): 5,540 lbf |
|thrust=Take-off Thrust(Sea Level Static): 5,540 lbf (27.7 kN) |
||
|compression= |
|compression= 11.5:1 (HP compressor) |
||
|bypass=4.2:1 |
|||
|aircon= |
|||
|aircon=182 lb/s (82.5 kg) |
|||
|turbinetemp= |
|turbinetemp= |
||
|fuelcon= |
|fuelcon= |
||
| Line 68: | Line 70: | ||
{{refbegin}} |
{{refbegin}} |
||
* Gunston, Bill. ''World Encyclopedia of Aero Engines''. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}} |
* 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}}. |
|||
{{refend}} |
{{refend}} |
||
{{Rolls-Royce plc aeroengines}} |
{{Rolls-Royce plc aeroengines}} |
||
| ⚫ | |||
[[Category:High-bypass turbofan engines]] |
[[Category:High-bypass turbofan engines]] |
||
| ⚫ | |||
[[Category:1970s turbofan engines]] |
[[Category:1970s turbofan engines]] |
||
Revision as of 15:52, 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 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)
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(Sea Level Static): 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)
See also
Related lists
References
Wikimedia Commons has media related to Rolls-Royce RB401.
Notes
- ^ Gunston 1989, p.155.
- ^ http://www.flightglobal.com/pdfarchive/view/1979/1979%20-%202715.html
- ^ 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.