31:
105:
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
106:
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.
405:
400:
371:
716:
364:
97:
Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled.
94:. RB.401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB.401-07 was taken.
685:
721:
357:
342:
428:
328:
39:
691:
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601:
291:
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258:
91:
349:
678:
616:
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238:
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584:
710:
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83:
629:
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578:
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516:
505:
167:
163:
Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes
392:
49:
379:
176:
205:
90:
started to develop in the mid-1970s as a replacement for the
187:
Hydromechanical with provision for electronic monitoring
323:. Cambridge, England. Patrick Stephens Limited, 1989.
181:
Two-stage LP, single-stage HP with air-cooled blades
708:
337:, London, Jane's Publishing Company Ltd, 1984.
193:Self-contained (tank, pumps,filters and cooler)
365:
109:
372:
358:
123:
38:Rolls-Royce RB.401 turbofan engine at the
100:
717:Rolls-Royce aircraft gas turbine engines
335:Jane's All the World's Aircraft 1984-85.
709:
16:1970s British turbofan aircraft engine
353:
210:Take-off thrust: 5,540 lbf (24.7 kN)
13:
321:World Encyclopedia of Aero Engines
14:
738:
40:Rolls-Royce Heritage Trust, Derby
692:Rolls-Royce Limited aero engines
29:
312:
686:Joint development aero engines
299:
285:
276:
197:
132:High-bypass two-spool turbofan
1:
264:
154:
144:32.4 in (823 mm) (fan casing)
722:High-bypass turbofan engines
295:, 1979. www.flightglobal.com
7:
626:Aero-derivative industrial
247:
10:
743:
696:Rolls-Royce Heritage Trust
110:Specifications (RB.401-07)
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594:
515:
391:
37:
28:
23:
269:
259:List of aircraft engines
124:General characteristics
727:1970s turbofan engines
595:Other fan-type engines
239:Thrust-to-weight ratio
219:11.5:1 (HP compressor)
215:Overall pressure ratio
101:Design and development
381:Rolls-Royce Holdings
282:Gunston 1989, p.155.
684:Symbol ‡ indicates
677:Symbol † indicates
333:Taylor, John W.R.
305:Taylor 1984, p.852
234:182 lb/s (82.5 kg)
138:60.8 in (1,545 mm)
77:Rolls-Royce RB.401
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69:21 December 1975
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150:985 lb (447 kg)
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253:Related lists
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86:engine which
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56:Manufacturer
55:
54:
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630:gas turbines
466:Trent series
444:
386:and aircraft
384:aero engines
334:
320:
313:Bibliography
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237:
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224:Bypass ratio
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84:business jet
76:
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628:and marine
521:Turboshafts
456:Spey Junior
198:Performance
191:Oil system:
161:Compressor:
148:Dry weight:
88:Rolls-Royce
60:Rolls-Royce
711:Categories
617:LiftSystem
517:Turboprops
500:Trent 7000
490:Trent 1000
265:References
185:Fuel type:
168:Combustors
155:Components
66:First run
690:See also
495:Trent XWB
485:Trent 900
480:Trent 800
475:Trent 700
470:Trent 500
406:Advance 3
401:Advance 2
393:Turbofans
142:Diameter:
115:Data from
81:two-spool
658:Aircraft
533:variants
248:See also
204:Maximum
50:Turbofan
681:engines
679:Allison
539:AE 2100
531: (
411:AE 3007
177:Turbine
172:Annular
136:Length:
24:RB.401
612:RB3011
607:RB2011
551:MTR390
341:
327:
293:Flight
206:thrust
118:Jane's
665:ACCEL
648:WR-21
602:RB529
585:TP400
562:RR500
557:RR300
506:V2500
450:RJ500
445:RB401
440:RB282
435:RB183
423:EJ200
417:BR700
270:Notes
243:5.6:1
228:4.2:1
130:Type:
92:Viper
46:Type
694:and
638:MT30
579:T800
573:T406
545:M250
429:F136
339:ISBN
325:ISBN
75:The
643:MT7
567:T56
529:501
461:Tay
713::
535:)†
650:‡
587:‡
581:‡
575:†
569:†
553:‡
547:†
541:†
519:/
508:‡
502:)
468:(
452:‡
431:‡
425:‡
419:‡
413:†
373:e
366:t
359:v
345:.
241::
226::
217::
208::
179::
170::
120:.
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
