Rolls-Royce RB401: Difference between revisions
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{{short description|1970s British turbofan aircraft engine}} |
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The '''RB401''' was a business jet engine which [[Rolls-Royce]] started to develop in the mid-1970's. |
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{{Use dmy dates|date=August 2017}} |
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{{Use British English|date=August 2017}} |
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{|{{Infobox Aircraft Begin |
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|name= RB.401 |
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|image= Rolls-Royce RB.401 RRHT Derby.jpg |
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|caption= Rolls-Royce RB.401 turbofan engine at the [[Rolls-Royce Heritage Trust, Derby]] |
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}}{{Infobox Aircraft Engine |
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|type=[[Turbofan]] |
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|manufacturer=[[Rolls-Royce Limited|Rolls-Royce]] |
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|first run= 21 December 1975 |
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|major applications= |
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|number built = |
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|program cost = |
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|unit cost = |
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|developed from = |
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|developed into = |
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|variants with their own articles = |
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}} |
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|} |
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The '''Rolls-Royce RB.401''' was a British [[Spool (aeronautics)|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. |
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⚫ | Although the basic |
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==Design and development== |
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Leading particulars for -07 variant were as follows: |
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⚫ | 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. |
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==Specifications (RB.401-07)== |
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Fan Diameter: 32.4in |
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{{jetspecs |
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|ref=''Jane's''.<ref>Taylor 1984, p.852</ref> |
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|type=High-bypass two-spool turbofan |
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|length=60.8 in (1,545 mm) |
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|diameter=32.4 in (823 mm) (fan casing) |
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|weight=985 lb (447 kg) |
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|compressor=Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes |
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|combustion=Annular |
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|turbine=Two-stage LP, single-stage HP with air-cooled blades |
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|fueltype=Hydromechanical with provision for electronic monitoring |
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|oilsystem=Self-contained (tank, pumps,filters and cooler) |
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|power= |
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|thrust=Take-off thrust: 5,540 lbf (24.7 kN) |
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|compression= 11.5:1 (HP compressor) |
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|bypass=4.2:1 |
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|aircon=182 lb/s (82.5 kg) |
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|turbinetemp= |
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|fuelcon= |
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|specfuelcon= |
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|power/weight= |
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|thrust/weight=5.6:1 |
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}} |
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==See also== |
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Take-off Thrust: 5540lbf, flat-rated to ISA+15C |
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{{Aircontent |
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|related= |
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|similar engines= |
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Cruise Thrust: 1128lbf (Mach 0.7, 40000ft, ISA+10C) |
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|lists= |
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* [[List of aircraft engines]] |
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|see also= |
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}} |
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==References== |
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{{Commons category}} |
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===Notes=== |
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{{reflist}} |
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===Bibliography=== |
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{{refbegin}} |
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* Gunston, Bill. ''World Encyclopedia of Aero Engines''. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}} |
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* 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}}. |
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{{refend}} |
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{{Rolls-Royce plc aeroengines}} |
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[[Category:Rolls-Royce aircraft gas turbine engines|RB401]] |
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[[Category:High-bypass turbofan engines]] |
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[[Category:1970s turbofan engines]] |
Latest revision as of 08:00, 24 September 2024
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 | 21 December 1975 |
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
[edit]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)
[edit]Data from Jane's.[3]
General characteristics
- Type: High-bypass two-spool turbofan
- Length: 60.8 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 (24.7 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
[edit]Related lists
References
[edit]Notes
[edit]- ^ Gunston 1989, p.155.
- ^ Flight, 1979. www.flightglobal.com
- ^ Taylor 1984, p.852
Bibliography
[edit]- 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.