简介：TheeffectoffrequencyandsampleshapeonfatiguebehaviorsofDZ125superalloyaresystematicallystudied.Theresultsshowthatfatiguefracturestilloccursabovethecycleof10~8fortestscarriedoutatthefrequencyoff=20kHzandstressratioR=-1,sothetraditionalfatiguelimitatcycleof10~7isnotappropriateforfatiguedesign.Fatiguefracturesurfacesareperpendiculartostressaxisforcylindricalandplatespecimens,andthefatiguecracksoriginatefromtheextrasurfaceofthespecimens.Fatiguecrackisapttopropagatefromcuttingdirectiontoforwarddirection,whichoccursmainlyinthesecondpropagationstageathigherstressamplitude.ThereisanobviousfrequencyeffectforDZ125superalloy.Thehigherthetestfrequencyis,themoreserioustheeffectoffrequencyonfatiguebehaviorsofthealloy.Afterthefrequencycorrection,theultra-highcyclefatigueS-NcurvewellcoincidewiththetraditionalfatigueS-Ncurve.

简介：Thethermalprotectionperformanceofsuperalloyhoneycombstructureinhigh-temperatureenvironmentsareimportantforthermalprotectiondesignofhigh-speedaircrafts.Byusingaself-developedtransientaerodynamicthermalsimulationsystem,thethermalprotectionperformanceofsuperalloyhoneycombpanelwastestedinthispaperatdifferenttransientheatingratesrangingfrom5℃/sto30℃/s,withthemaximuminstantaneoustemperaturereaching950℃.Furthermore,thethermalprotectionperformanceofsuperalloyhoneycombstructureundersimulatedthermalenvironmentswascomputedfordifferenthighheatingratesbyusing3Dfiniteelementmethod,andacomparisonbetweencalculationalandexperimentalresultswascarriedout.Theresultsofthisresearchprovideanimportantreferenceforthedesignofthermalprotectionsystemscomprisingsuperalloyhoneycombpanel.

简介：基于镍的单个水晶superalloy与的低周期的疲劳(LCF)行为[001]取向在T0掳C的中间的温度和T0+的更高的温度被学习在10的经常的低紧张率下面的250掳C?3s?1在周围的空气。superalloy展出了依赖于温度并且使用紧张振幅的周期的紧张压缩不对称现象。破裂表面上的分析证明表面和表面下的扔micropores是主要裂缝开始地点。内部Ta富有的碳化物经常在所有标本被观察。骨折的二种不同类型被frac-togaphy建议。一种类型被模式描绘--我与一台用显微镜裂开在T0+的不平的表面250掳C。而在更低的温度T0C的另外的类型赞成了中的一个或几八面{111}飞机，与正常模式相对照--我生长模式典型地在低装载观察了频率(几Hz)。为二个裂开的模式的失败机制纬鈥?正在砍在T0+在矩阵和纬/纬鈥?接口在T0掳C和裂开的反对ned和矩阵猛抛250掳C。

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