Rolls-Royce RB401: Difference between revisions

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

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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

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: 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

References

Notes

^ Gunston 1989, p.155.
^ Flight, 1979. www.flightglobal.com
^ 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.

[1] Gunston 1989, p.155.

[2] Flight, 1979. www.flightglobal.com

[3] Taylor 1984, p.852

[1]

[2]

[3]

@@ Line 1: / Line 1: @@
+{{short description|1970s British turbofan aircraft engine}}
-{{Cleanup|date=January 2007}}
+<!-- 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 =
+}}
+|}
-The '''RB401''' was a business jet engine which [[Rolls-Royce Limited|Rolls-Royce]] started to develop in the mid-[[1970s]].
+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.
-RB401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB401-07 was taken.
+==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.
-Leading particulars for -07 variant were as follows:
+==Specifications (RB.401-07)==
-Fan Diameter: 32.4 in
+{{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(Sea Level Static): 5,540 lbf, flat-rated to ISA+15C
+{{Aircontent
+|related=
+|similar engines=
-Cruise Thrust: 1128lbf (Mach 0.7, 40,000 ft, ISA+10C)
+|lists=
+* [[List of aircraft engines]]
+|see also=
+}}
-Bypass Ratio: ~4
+==References==
-Overall Pressure Ratio: ~20:1
+{{Commons category}}
+===Notes===
+{{reflist}}
+===Bibliography===
-Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled.
-{{RRaeroengines}}
+{{refbegin}}
+* Gunston, Bill. ''World Encyclopedia of Aero Engines''. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}}
-{{aero-specs}}
+* 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]]
-{{engine-aircraft-stub}}

v t e Rolls-Royce Holdings aero engines and aircraft
Turbofans	Advance 2 Advance 3 AE 3007† BR700‡ EJ200‡ F136‡ RB183 RB282 RB401 RJ500‡ Spey Junior Tay Trent series (Trent 500 Trent 700 Trent 800 Trent 900 Trent 1000 Trent XWB Trent 7000) V2500‡
Turboprops/Turboshafts	501 (variants)† AE 2100† M250† MTR390‡ RR300 RR500 T56† T406† T800‡ TP400‡
Other fan-type engines	RB529 RB2011 RB3011 LiftSystem
Aero-derivative industrial and marine gas turbines	MT30 MT7 WR-21‡
Aircraft	ACCEL
Symbol † indicates Allison engines Symbol ‡ indicates Joint development aero engines See also Rolls-Royce Limited aero engines and Rolls-Royce Heritage Trust