涂层扩散热处理工艺对DD6单晶高温合金组织和力学性能的影响
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摘要
研究了870℃/6 h涂层扩散热处理工艺对第二代镍基DD6单晶高温合金(简称DD6合金)组织和性能的影响。研究结果表明,采用870℃/6 h涂层扩散热处理工艺处理后,DD6合金的显微组织、760℃拉伸性能、980℃/250 MPa持久性能、700℃高周疲劳性能无明显变化。DD6合金760℃拉伸断裂类型为准解理断裂,980℃/250 MPa持久断裂类型为韧窝断裂,700℃高周疲劳断裂类型为准解理断裂。涂层扩散处理没有改变DD6合金的断裂机制。
The effect of coating diffusion heat treatment process of 870 ℃/6 h on microstructure and mechanical property of a second generation nickel-based DD6 single crystal superalloy(DD6 alloy for short) has been investigated. The results indicates that the DD6 alloy shows no obvious change on the microstructure, tensile properties at 760 ℃, stress rupture properties at 980 ℃/250 MPa and high cycle fatigue(HCF) properties at 700 ℃ after the coating diffusion heat treatment of 870 ℃/6 h. The tensile fracture mechanism of the alloy at 760 ℃ is quasi-cleavage fracture. The stress rupture mechanism at 980 ℃/250 MPa is dimple mode. The HCF fracture mechanism at 700 ℃ is quasi-cleavage fracture. The fracture mechanisms of the DD6 alloy aren't changed by coating diffusion treatment.
The effect of coating diffusion heat treatment process of 870 ℃/6 h on microstructure and mechanical property of a second generation nickel-based DD6 single crystal superalloy(DD6 alloy for short) has been investigated. The results indicates that the DD6 alloy shows no obvious change on the microstructure, tensile properties at 760 ℃, stress rupture properties at 980 ℃/250 MPa and high cycle fatigue(HCF) properties at 700 ℃ after the coating diffusion heat treatment of 870 ℃/6 h. The tensile fracture mechanism of the alloy at 760 ℃ is quasi-cleavage fracture. The stress rupture mechanism at 980 ℃/250 MPa is dimple mode. The HCF fracture mechanism at 700 ℃ is quasi-cleavage fracture. The fracture mechanisms of the DD6 alloy aren't changed by coating diffusion treatment.
引文
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[4]ARGENCE D,VERNAULT C,DESVALLEES Y,et al.MC-NG:Generation single crystal superalloy for future aeronautical turbine blades and vanes[C]//Pollock T M,KISSINGER R D,BOWMAN R R,GREEN K A,MCLEAN M,OLSON S,SCHIRRA J J.Superalloys2000.Warrendale,PA:TMS,2000:829-837.
[5]WALSTON S,CETEL A,MACKAY R,et al.Joint development of a fourth generation single crystal superalloy[C]//GREEN K A,POLLOK T M,HARADAH,HOWSON T W,REED R C,SCHIRRA J J,WALSTON S.Superalloys2004.Pennsylvania,PA:TMS,2004:15-24.
[6]史振学,刘世忠.过热处理对单晶高温合金拉伸性能的影响[J].有色金属材料与工程,2017,38(6):321-325.
[7]PETERS M,LEYENS C,SCHULZ U,et al.EB-PVDthermal barrier coating for aeroengines and gas turbines[J].Advanced Engineering Materials,2001,3(4):193-204.
[8]孙永井,李秋实,郭洪波,等.Ni-Al涂层与单晶合金互扩散行为及其对界面合金组织稳定性的影响[J].中国腐蚀与防护学报,2016,36(5):497-504.
[9]LI J R,ZHONG Z G,TANG D Z,et al.A low-cost second generation single crystal superalloy DD6[C]//Pollock T M,KISSINGER R D,BOWMAN R R,GREEN K A,MCLEAN M,OLSON S,SCHIRRA J J.Superalloys 2000.Warrendale,PA:TMS,2000:777-783.
[10]LI J R,ZHAO J Q,LIU S Z,et al.Effects of low angle boundary on the mechanicla properties of single crystal superalloy DD6[C]//REED R C,GREEN K A,CARONP,GABB T P,FAHRMANN M G,HURON E S,WOODARD S A.Superalloys2008.Pennysylvania,PA:TMS,2008:443-451.
[11]WAN J S,YUE Z F.A low-cycle fatigue life model of nickel-based single crystal superalloys under multiaxial stress state[J].Materials Science and Engineering A,2005,392:145-149.
[12]刘世忠,史振学,熊继春,等.一种单晶高温合金的组织和持久性能[J].有色金属科学与工程,2017,8(1):118-121.
[13]丁智平,刘义伦,尹泽勇.镍基单晶高温合金蠕变-疲劳寿命评估方法进展[J].机械强度,2003,25(3):254-259.
[14]钟群鹏,赵子华.断口学[M].北京:高等教育出版社,2006.
[15]WASSON A J,FUCHS G E.The effect of carbide morphologies on elevated temperature tensile and fatigue behavior of a modified single crystal Ni-base superalloy[C]//REED R C,GREEN K A,CARON P,GABB P,FAHRMANN G,HURON E S,WOODARD S A.Superalloys2008.Pennsylvania,PA:TMS,2008:489-497.