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{{short description|1970s British turbofan aircraft engine}}
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{{Use dmy dates|date=August 2017}}
⚫
{{seealso|Rolls-Royce Tay (turbojet)}}
{{Use British English|date=August 2017}}
{|{{Infobox Aircraft Begin
{|{{Infobox Aircraft Begin
|name= RB.401
|name= RB.401
|image=
|image= Rolls-Royce RB.401 RRHT Derby.jpg
|caption= Rolls-Royce RB.401 turbofan engine at the [[Rolls-Royce Heritage Trust, Derby]]
|caption=
}}{{Infobox Aircraft Engine
}}{{Infobox Aircraft Engine
|type=[[Turbofan]]
|type=[[Turbofan]]
|manufacturer=[[Rolls-Royce plc|Rolls-Royce]]
|manufacturer=[[Rolls-Royce Limited|Rolls-Royce]]
|first run= {{avyear|1975}}
|first run= 21 December 1975
|major applications=
|major applications=
|number built =
|number built =
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|developed into =
|developed into =
|variants with their own articles =
|variants with their own articles =

}}
}}
|}
|}


The '''Rolls-Royce RB.401''' was a business jet engine which [[Rolls-Royce plc|Rolls-Royce]] started to develop in the mid-1970s.<ref>Gunston 1989, p.155.</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.
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.
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==
Although the basic configurations of both engines were almost identical, the -07 variant had a larger fan diameter. The -06 version HP compressor was based on the 8 stage version of RC34B research compressor, unscaled, whereas the -07 was a scaled-up unit. A single stage fan, driven by 2 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.
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.141-07)==
==Specifications (RB.401-07)==
{{jetspecs
{{jetspecs
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<!-- 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> -->
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|ref=''Jane's''.<ref>Taylor 1984, p.852</ref>
|type=High bypass Turbofan
|type=High-bypass two-spool turbofan
|length=
|diameter=32.4 in (fan)
|length=60.8 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, flat-rated to ISA+15C
|thrust=Take-off thrust: 5,540 lbf (24.7 kN)
|compression=~20:1
|compression= 11.5:1 (HP compressor)
|bypass=4.2:1
|aircon=
|aircon=182 lb/s (82.5 kg)
|turbinetemp=
|turbinetemp=
|fuelcon=
|fuelcon=
|specfuelcon=
|specfuelcon=
|power/weight=
|power/weight=
|thrust/weight=
|thrust/weight=5.6:1
}}
}}


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==References==
==References==
{{Commons category}}
===Notes===
===Notes===
{{reflist}}
{{reflist}}

===Bibliography===
===Bibliography===
{{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}}
{{RRaeroengines}}
{{aviation lists}}

{{aero-specs}}
{{engine-aircraft-stub}}


[[Category:Rolls-Royce aircraft gas turbine engines|RB401]]
[[Category:High-bypass turbofan engines]]
[[Category:High-bypass turbofan engines]]
[[Category:Rolls-Royce aircraft gas turbine engines]]
[[Category:1970s turbofan engines]]

Latest revision as of 08:00, 24 September 2024

RB.401
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

See also

[edit]

Related lists

References

[edit]
Wikimedia Commons has media related to Rolls-Royce RB401.

Notes

[edit]
  1. ^ Gunston 1989, p.155.
  2. ^ Flight, 1979. www.flightglobal.com
  3. ^ 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.
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