26:
546:
213:
Work on this engine began in earnest in 1986, and a demonstrator engine was built and tested in 1987. IHI was formally awarded a contract for the engine in 1992, after spending the previous years developing and testing the engine internally.
627:
Kashikawa, I., & Akagi, M. (1995). Research on a High Thrust-to-Weight Ratio Small
Turbofan Engine. Presented at the 31st AlAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San Diego, CA: American Institute of Aeronautics and
255:
The two-stage fan uses wide chord blades, and both the production F3 and the advanced XF3-400 use the same fan. Unlike the fan, the five-stage compressor differs between the F3 and the XF3-400, with the advanced XF3-400 benefiting from 3D
802:
267:
blades, and they are cooled by a thin film of air from inside of the blades. The low-pressure turbine blades, like the high-pressure compressor, were improved between the F3 and the XF3-400 using 3D CFD.
252:, which feeds a single-stage high-pressure turbine followed by a single-stage low-pressure turbine. The XF3-400 variant includes an afterburner after the low-pressure turbine, the production F3 does not.
654:
158:
The production engine was designated the F3-30 (alternatively, the F3-IHI-30), and it first flew in the XT-4 aircraft in 1985. Production of the qualified engine also began in 1985.
248:. It features a two-stage fan (low-pressure compressor) on the low-pressure shaft, followed by a five-stage high-pressure compressor on the high-pressure shaft. The engine uses an
795:
169:
problem, leading to the turbine blade failures. The blades were strengthened and modified to dampen the vibrations. The engine, and the aircraft, returned to service in 1990.
172:
Beginning in 1999, IHI began upgrading the fielded engines with a new high-pressure turbine to increase their service life. This variant of the engine was known as the
788:
316:
Supersonic technology demonstrator variant of the engine. Much higher thrust than the production F3. Includes an afterburner and several aerodynamic upgrades.
685:
195:
Soon after IHI began working on the XF-3, they began developing a more powerful variant of the engine as a technology demonstrator for a theoretical
139:
Ishikawajima-Harima began developing a small turbofan engine in the late 1970s as a competitor for the new jet trainer aircraft being developed by
573:
Hamada, T., Akagi, M., Toda, D., Shimazaki, H., & Ohmomo, M. (1989). T-4 Inlet/Engine
Compatibility Flight Test Results. Presented at the
206:
version of the XF-3, producing around 7,600 lbf (34 kN) of thrust. One distinctive quality of this engine was that it was to have a
283:
Early developmental designation of what became the F3-IHI-30. Several different configurations were considered in this phase of the program.
915:
165:
failed, forcing the aircraft to make emergency landings. An investigation revealed that the turbine section was suffering from a vibration
637:
221:. Adding the afterburner is the primary reason why the maximum thrust of the -400 is much higher than the -30. Other changes included
447:
910:
920:
678:
257:
226:
811:
663:
161:
After the engine and aircraft were in production there were several incidents where one or two of the high pressure
780:
140:
671:
515:
155:, but later models (including the model selected for the XT-4) produced 3,600 lbf (16 kN) of thrust.
131:
engine, the XF3, was manufactured in 1981 and first flew in the XT-4 in July 1985. About 550 have been built.
879:
498:
144:
834:
736:
456:
429:
207:
598:
586:
558:
856:
889:
769:
759:
713:
486:
476:
196:
151:
trainer. The early developmental models of the engine produced 2,600 pounds-force (12 kN) of
884:
764:
731:
481:
124:
697:
503:
385:
233:
222:
199:
817:
694:
117:
63:
217:
The primary difference between the XF3-400 and the standard F3-30 is the inclusion of an
264:
202:. This engine was designated the XF3-400. It was designed to be a higher performance,
904:
438:
326:
290:
148:
121:
106:
83:
814:
218:
203:
229:
techniques, and improved temperature performance in the high-pressure turbine.
848:
561:. (1982, December 11). Flight International, 1677. Accessed February 4, 2010.
844:
397:
392:
249:
166:
128:
589:. (1989, November 29). Flight International, 16. Accessed February 4, 2010.
143:. The developmental engine was named the XF3, and it was selected over the
601:. (1990, January 17). Flight International, 27. Accessed February 4, 2010.
866:
826:
746:
723:
705:
352:
245:
109:
41:
299:
Production version of the engine with an upgraded high pressure turbine.
25:
640:. (1998, October 21). Flight International. Retrieved February 4, 2010.
403:
162:
420:
152:
388:, 2 stage, low pressure compressor, 5 stage high pressure compressor
577:, Monterey, CA: American Institute of Aeronautics and Astronautics.
408:
single stage high pressure turbine, two stage low pressure turbine
180:
113:
53:
225:
and turbine blades that were aerodynamically optimized using 3D
784:
667:
271:
Both the F3 and the XF3-400 use a FADEC for engine control.
179:
In 2003, IHI began updating the engine with a more advanced
305:
Production version of the engine with an improved FADEC.
549:) Edited January 13, 2009. Accessed February 9, 2010.
695:
Ishikawajima-Harima Heavy
Industries/IHI Corporation
865:
843:
825:
745:
722:
704:
575:
AIAA/ASME/SAE/ASEE 25th Joint
Propulsion Conference
244:The F3 is a two-shaft (or two spool) low-bypass
210:of 7:1, higher than any similarly sized engine.
183:(FADEC). This updated engine was designated the
289:Production variant of the engine. Used by the
796:
679:
103:Ishikawajima-Harima Heavy Industries (IHI) F3
8:
236:was also being integrated into the XF3-400.
803:
789:
781:
686:
672:
664:
653:. Aviation Week & Space Technology. (
638:Japan stalls future fighter demonstrator
537:
535:
533:
531:
527:
623:
621:
619:
617:
615:
613:
611:
609:
607:
569:
567:
15:
263:The high-pressure turbine blades are
181:Full Authority Digital Engine Control
7:
118:Ishikawajima-Harima Heavy Industries
14:
587:Japan Tackles F3 engine problems
559:Japanese trainer engine selected
24:
599:Japan finds fix for T-4 trainer
1:
657:). Accessed February 2, 2010.
425:3,680 lbf (16.4 kN)
258:computational fluid dynamics
232:A 1998 report revealed that
227:computational fluid dynamics
916:Low-bypass turbofan engines
937:
333:Specifications (F3-IHI-30)
651:2010 Aerospace Sourcebook
448:Specific fuel consumption
141:Kawasaki Heavy Industries
32:
23:
18:
516:List of aircraft engines
499:SNECMA Turbomeca Larzac
343:General characteristics
145:SNECMA Turbomeca Larzac
33:IHI F3 Turbofan Engine
911:1980s turbofan engines
457:Thrust-to-weight ratio
430:Overall pressure ratio
208:thrust-to-weight ratio
135:Design and development
147:in 1982 to power the
921:IHI aircraft engines
260:(CFD) improvements.
125:jet trainer aircraft
112:engine developed in
543:Jane's Aero Engines
487:IHI Corporation XF9
477:IHI Corporation XF5
471:Related development
820:designation system
493:Comparable engines
482:IHI Corporation F7
79:Major applications
898:
897:
812:Japanese military
778:
777:
655:subscription page
547:subscription page
250:annular combustor
99:
98:
928:
805:
798:
791:
782:
688:
681:
674:
665:
658:
647:
641:
635:
629:
625:
602:
596:
590:
584:
578:
571:
562:
556:
550:
539:
504:NPO Saturn AL-55
234:thrust vectoring
92:
80:
50:
28:
16:
936:
935:
931:
930:
929:
927:
926:
925:
901:
900:
899:
894:
861:
839:
821:
818:aircraft engine
809:
779:
774:
741:
718:
700:
692:
662:
661:
648:
644:
636:
632:
626:
605:
597:
593:
585:
581:
572:
565:
557:
553:
540:
529:
524:
468:
415:
379:
372:750 lb (340 kg)
345:
335:
323:
277:
242:
193:
137:
90:
78:
64:IHI Corporation
49:National origin
48:
12:
11:
5:
934:
932:
924:
923:
918:
913:
903:
902:
896:
895:
893:
892:
887:
882:
877:
871:
869:
863:
862:
860:
859:
853:
851:
841:
840:
838:
837:
831:
829:
823:
822:
810:
808:
807:
800:
793:
785:
776:
775:
773:
772:
767:
762:
757:
751:
749:
743:
742:
740:
739:
734:
728:
726:
720:
719:
717:
716:
710:
708:
702:
701:
693:
691:
690:
683:
676:
668:
660:
659:
642:
630:
603:
591:
579:
563:
551:
526:
525:
523:
520:
519:
518:
507:
506:
501:
490:
489:
484:
479:
467:
464:
463:
462:
453:
452:0.7 lb/(lbf h)
444:
435:
426:
414:
411:
410:
409:
400:
389:
378:
375:
374:
373:
367:
361:
360:79 in (200 cm)
355:
344:
341:
334:
331:
330:
329:
322:
319:
318:
317:
314:
311:
309:
306:
303:
300:
297:
294:
287:
284:
281:
276:
273:
265:single-crystal
241:
238:
192:
189:
163:turbine blades
136:
133:
97:
96:
93:
87:
86:
81:
75:
74:
71:
67:
66:
61:
57:
56:
51:
45:
44:
39:
35:
34:
30:
29:
21:
20:
13:
10:
9:
6:
4:
3:
2:
933:
922:
919:
917:
914:
912:
909:
908:
906:
891:
888:
886:
883:
881:
878:
876:
873:
872:
870:
868:
864:
858:
855:
854:
852:
850:
846:
842:
836:
833:
832:
830:
828:
824:
819:
816:
813:
806:
801:
799:
794:
792:
787:
786:
783:
771:
768:
766:
763:
761:
758:
756:
753:
752:
750:
748:
744:
738:
735:
733:
730:
729:
727:
725:
721:
715:
712:
711:
709:
707:
703:
699:
696:
689:
684:
682:
677:
675:
670:
669:
666:
656:
652:
646:
643:
639:
634:
631:
628:Astronautics.
624:
622:
620:
618:
616:
614:
612:
610:
608:
604:
600:
595:
592:
588:
583:
580:
576:
570:
568:
564:
560:
555:
552:
548:
544:
538:
536:
534:
532:
528:
521:
517:
514:
513:
512:
511:
510:Related lists
505:
502:
500:
497:
496:
495:
494:
488:
485:
483:
480:
478:
475:
474:
473:
472:
465:
460:
458:
454:
451:
449:
445:
442:
440:
436:
433:
431:
427:
424:
422:
417:
416:
412:
407:
405:
401:
399:
396:
394:
390:
387:
384:
381:
380:
376:
371:
368:
366:25 in (63 cm)
365:
362:
359:
356:
354:
350:
347:
346:
342:
340:
339:
332:
328:
325:
324:
320:
315:
312:
310:
307:
304:
301:
298:
295:
292:
288:
285:
282:
279:
278:
274:
272:
269:
266:
261:
259:
253:
251:
247:
239:
237:
235:
230:
228:
224:
220:
215:
211:
209:
205:
201:
198:
190:
188:
186:
182:
177:
175:
170:
168:
164:
159:
156:
154:
150:
146:
142:
134:
132:
130:
126:
123:
119:
115:
111:
108:
104:
94:
89:
88:
85:
82:
77:
76:
72:
69:
68:
65:
62:
60:Manufacturer
59:
58:
55:
52:
47:
46:
43:
40:
37:
36:
31:
27:
22:
17:
874:
754:
698:aero engines
650:
645:
633:
594:
582:
574:
554:
542:
509:
508:
492:
491:
470:
469:
455:
446:
439:Bypass ratio
437:
428:
418:
402:
391:
382:
369:
363:
357:
348:
337:
336:
327:Kawasaki T-4
321:Applications
291:Kawasaki T-4
270:
262:
254:
243:
231:
216:
212:
204:afterburning
194:
184:
178:
173:
171:
160:
157:
138:
127:. The first
122:Kawasaki T-4
102:
100:
91:Number built
84:Kawasaki T-4
849:Turboshafts
815:gas turbine
413:Performance
383:Compressor:
370:Dry weight:
351:twin-spool
219:afterburner
905:Categories
845:Turboprops
649:"IHI F3".
522:References
393:Combustors
377:Components
302:F3-IHI-30C
296:F3-IHI-30B
223:compressor
197:supersonic
185:F3-IHI-30C
174:F3-IHI-30B
107:low bypass
70:First run
867:Turbofans
827:Turbojets
747:Turbofans
724:Turbojets
706:Motorjets
364:Diameter:
338:Data from
286:F3-IHI-30
167:resonance
129:prototype
541:IHI F3.
466:See also
419:Maximum
353:turbofan
275:Variants
246:turbofan
120:for the
110:turbofan
42:Turbofan
404:Turbine
398:annular
358:Length:
313:XF3-400
200:fighter
191:XF3-400
714:Tsu-11
421:thrust
308:IHI-17
240:Design
153:thrust
732:Ne-20
443:0.9:1
386:axial
349:Type:
114:Japan
105:is a
95:~550
73:1981
54:Japan
38:Type
434:11:1
149:XT-4
101:The
857:TS1
770:XF9
545:. (
461:4.9
280:XF3
116:by
19:F3
907::
890:F9
885:F7
880:F5
875:F3
835:J3
765:F7
760:F5
755:F3
737:J3
606:^
566:^
530:^
187:.
176:.
847:/
804:e
797:t
790:v
687:e
680:t
673:v
459::
450::
441::
432::
423::
406::
395::
293:.
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
