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{{short description|1970s British turbofan aircraft engine}}
<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. -->
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{{Use dmy dates|date=August 2017}}
{{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 Limited|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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|}
|}


The '''Rolls-Royce RB.401''' was a business jet engine which [[Rolls-Royce Limited|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 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.
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)==
==Specifications (RB.401-07)==
{{jetspecs
{{jetspecs
<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
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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}}


[[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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