Jump to content

Rolls-Royce RB401: Difference between revisions

From Wikipedia, the free encyclopedia
Content deleted Content added
No edit summary
m Reverted edit by Hello World Earth tinybutmighty (talk) to last version by Praemonitus
 
(41 intermediate revisions by 19 users not shown)
Line 1: Line 1:
{{short description|1970s British turbofan aircraft engine}}
The '''RB401''' was a business jet engine which [[Rolls-Royce]] started to develop in the mid-1970's.
<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. -->
{{Use dmy dates|date=August 2017}}
{{Use British English|date=August 2017}}
{|{{Infobox Aircraft Begin
|name= RB.401
|image= Rolls-Royce RB.401 RRHT Derby.jpg
|caption= Rolls-Royce RB.401 turbofan engine at the [[Rolls-Royce Heritage Trust, Derby]]
}}{{Infobox Aircraft Engine
|type=[[Turbofan]]
|manufacturer=[[Rolls-Royce Limited|Rolls-Royce]]
|first run= 21 December 1975
|major applications=
|number built =
|program cost =
|unit cost =
|developed from =
|developed into =
|variants with their own articles =
}}
|}


RB401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB401-07 was taken.
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.
Although the basic configurations of both engines were almost identical, the -07 variant had a larger fan diameter. A single stage fan, driven by 2 stage LP turbine, supercharged an 8 stage HP compressor, driven by a single stage transonic HP turbine. The combustor was annular and the co-annular exhaust featured a lightweight target type thrust reverser.


==Design and development==
Leading particulars for -07 variant were as follows:
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)==
Fan Diameter: 32.4in
{{jetspecs
<!-- 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> -->
|ref=''Jane's''.<ref>Taylor 1984, p.852</ref>
|type=High-bypass two-spool turbofan
|length=60.8 in (1,545 mm)
|diameter=32.4 in (823 mm) (fan casing)
|weight=985 lb (447 kg)
|compressor=Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes
|combustion=Annular
|turbine=Two-stage LP, single-stage HP with air-cooled blades
|fueltype=Hydromechanical with provision for electronic monitoring
|oilsystem=Self-contained (tank, pumps,filters and cooler)
|power=
|thrust=Take-off thrust: 5,540 lbf (24.7 kN)
|compression= 11.5:1 (HP compressor)
|bypass=4.2:1
|aircon=182 lb/s (82.5 kg)
|turbinetemp=
|fuelcon=
|specfuelcon=
|power/weight=
|thrust/weight=5.6:1
}}


==See also==
Take-off Thrust: 5540lbf, flat-rated to ISA+15C
{{Aircontent
|related=


|similar engines=
Cruise Thrust: 1128lbf (Mach 0.7, 40000ft, ISA+10C)
|lists=
* [[List of aircraft engines]]
|see also=


}}
Although ground testing of both the -06 and -07 continued into the early 80's, a lack of funds caused the project to be cancelled.

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

===Bibliography===
{{refbegin}}
* 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}}

{{Rolls-Royce plc aeroengines}}

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

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.