TA15钛合金两类组织对疲劳性能和断裂韧度的影响-张庆玲

TA15EffectofStructureonFatiguePropertiesandFractureToughnessforTA15TitaniumAlloy,(,100095)ZHANGQing-ling,LIXing-wu(BeijingInstituteofAeronauticalMaterials,Beijing100095,China):TA15,:S-N,;,,(656MPa)(565MPa),K1C,:;;;;:TG113.25:A:1001-4381(2007)07-0003-03Abstract:Effectoflamellarandb-imodalstructureonfatiguepropertiesandfracturetoughnesshavebeeninvestigatedforTA15titaniumalloy.Theresultsshowthatfatiguestrengthofb-imodalstruc-tureishigherthanlamellarstructureinthelowcycleregion.howeverthefatiguelimitoflamellarstructureishigherthanb-imodalstructureinthehighcycle.Thedamagetolerancepropertiesofla-mellararebetterthanb-imodalstructure,i.e.fracturetoughnessishigherandcrackgrowthrateisloweroflamellarstructure.Keywords:titaniumalloy;lamellarstructure;b-imodalstructure;fatigueproperties;fracturetough-ness,,:,;,;,2070,,,,,,,[1],()()[2-5],,,,,1TA15,,,500TA151,SEM,:R=0.1100Hz,3TA151TA15(/%)Table1CompositionofTA15titaniumalloy(massfraction/%)AlMoVZrTiOH6.561.622.102.15Bal0.080.004SEM,22.1TA151,S-N22,1106~2106,,,(656MPa)(565MPa)1TA15(a);(b)Fig.1TwotypicalmicrostructuresofTA15titaniumalloy(a)lamellarstructure;(b)b-imodalstructure2TA15S-NFig.2S-NcurvesoftwotypicalmicrostructuresforTA15titaniumalloy(Kt=1,R=0.1,f=130Hz),[6]:,,,,,,,,,,2,50MPa,,;,(656MPa)(565MPa),,;,,2TA15Table2TensilepropertiesoftwotypicalmicrostructuresforTA15titaniumalloyatRTStructurestypeb/MPa0.2/MPa5/%/%Lamellar93587511.126.1B-imodal99192515.447.32.23SEM,,4/200773TA15SEMTable3CyclicnumbersunderSEMforthetwotypicalmicrostructuresofTA15titaniumalloyTypeB-imodalLamellarCyclicnumbers/cycle7377653,,,,da/dN-N(3),;,,,3TA15SEMFig.3FatiguecrackgrowthrateunderSEMinthetwostructuresofTA15titaniumalloy2.3TA154,(0.08%),,,4TA15Table4FracturetoughnessoftwotypicalmicrostructureforTA15titaniumalloyTypeKIC/MPam1/2Lamellar92.3B-imodal82.0,(),,,,,(),,,,3(1)TA15S-N1106~2106,,,(656MPa)(565MPa)(2);,(3)TA15[1].[J].,2002,38(S1):4-11.[2]FILIPR,KUBIAKK,ZIAJIAWetal.Theeffectofmicrostruc-tureonthemechanicalpropertiesoftwo-phasetitaniumalloys[J].JournalofMaterialsProcessingTechnology,2003,133:84-89.[3]LTJERINGG.Influenceofprocessingonmicrostructureandmechanicalpropertiesof+titaniumalloys[J].MatSciEngA,1998,A243:32-45.[4]WANHILLRJH.Ambienttemperaturecrackgrowthintitan-iumalloysanditssignificanceforaircraftstructures[J].Aeronau-ticalJournal,1977,81:68-82.[5]CRICHLOWWJ.Highcyclefatiguepropertiesoftitaniuminaircraftapplication[A].JAFEERI,BURTEHM(Edited).T-itaniumScienceandTechnology[C].NewYork-London:PlenumPress,1973.1257-1270.[6]HINESJA,TJERINGG.PropagationofmicrocracksatstressamplitudesbelowtheconventionalfatiguelimitinT-i6A-l4V[J].FatigueFractEngngMaterStructure,1999,22:657-665.:2007-04-12;:2007-05-20:(1967),,,,,:817(100095)5TA15