服役透平叶片GTD111 DS合金再热恢复研究
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摘要
以服役透平叶片GTD111 DS定向合金材料为研究对象,采用光学显微镜和扫描电镜对简单再热恢复处理前后的叶片材料微观组织进行观察,并对合金材料显微硬度进行测试,研究再热恢复参数对γ'相(主要沉淀强化相)特征的影响规律,评估恢复态叶片材料的组织和性能.结果表明:固溶温度、冷却速度、时效温度和时间是再热恢复处理的关键参数;合适温度下的固溶处理可有效溶解粗大形变γ'相,并重新析出细小均匀的二次γ'相,同时避免初熔和再结晶;两级时效处理可优化双尺寸形态γ'相的尺寸、体积分数和立方度.恢复处理后叶片不同部位的组织和性能分布更加均匀,二次γ'相和三次γ'相的平均颗粒尺寸分别约为440和70nm,其体积分数分别约为35%和3%,硬度值处于409～417 HV范围内,高于叶根部位原始状态的硬度值.
Microstructure and microhardness of directionally solidified GTD111 DS superalloy after service exposure and different simple re-heat rejuvenation treatment for turbine blades were studied by light optical microscope,scanning electron microscopy(SEM),and vicker microhardness tester,respectively.Then the effect of rejuvenation conditions on microstructure characteristics of the precipitation strengthening phase γ' of directionally solidified superalloy in turbine blades was investigated,and the microstructure and properties of the rejuvenated blades material were evaluated.The results show that solution temperature,cooling rate,aging temperature and time are most important rejuvenation parameters of turbine blades.The solution treatment under proper temperature condition can dissolve effectively coarsened and deformed γ' phase,and re-precipitate fine secondary γ' phase,with initial melting and recrystallization avoided.Two-stage aging can optimize the size,volume fraction and cubic degree of the bimodal size γ' phase with coarse secondary γ' phase and fine tertiary γ' phase.After re-heat rejuvenation treatment,the microstructure of blades material becomes finer and more homogeneous,and material properties distribute more uniform.For different locations of the rejuvenated blades,the sizes of secondary γ' phase and tertiary γ' phase are about 440 and 70 nm,the volume fractions of secondary γ' phase and tertiary γ' phase are about 35% and 3%,and the microhardness values are all in range of 409～417 HV,which are even higher than that of virgin station in blades root.
Microstructure and microhardness of directionally solidified GTD111 DS superalloy after service exposure and different simple re-heat rejuvenation treatment for turbine blades were studied by light optical microscope,scanning electron microscopy(SEM),and vicker microhardness tester,respectively.Then the effect of rejuvenation conditions on microstructure characteristics of the precipitation strengthening phase γ' of directionally solidified superalloy in turbine blades was investigated,and the microstructure and properties of the rejuvenated blades material were evaluated.The results show that solution temperature,cooling rate,aging temperature and time are most important rejuvenation parameters of turbine blades.The solution treatment under proper temperature condition can dissolve effectively coarsened and deformed γ' phase,and re-precipitate fine secondary γ' phase,with initial melting and recrystallization avoided.Two-stage aging can optimize the size,volume fraction and cubic degree of the bimodal size γ' phase with coarse secondary γ' phase and fine tertiary γ' phase.After re-heat rejuvenation treatment,the microstructure of blades material becomes finer and more homogeneous,and material properties distribute more uniform.For different locations of the rejuvenated blades,the sizes of secondary γ' phase and tertiary γ' phase are about 440 and 70 nm,the volume fractions of secondary γ' phase and tertiary γ' phase are about 35% and 3%,and the microhardness values are all in range of 409～417 HV,which are even higher than that of virgin station in blades root.
引文
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[11]ZHOU Y,ZHANG Z,ZHAO Z H,et al.Effects of HIPtemperature on the microstructural evolution and property restoration of a Ni-based superalloy[J].Journal of Materials Engineering and Performance,2013,22(1):215-222.
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[13]KIM H I,PARK H S,KOO J M,et al.Microstructural investigation of GTD 111DS materials in the heat treatment conditions[J].Journal of Mechanical Science and Technology,2012,26(7):2019-2022.
[14]RUTTERT B,BURGER D,RONCERY L M,et al.Rejuvenation of creep resistance of a Ni-base single-crystal superalloy by hot isostatic pressing[J].Materials&Design,2017,134:418-425.
[15]GUO H M,ZHAO Y S,ZHENG S,et al.Effect of hot-isostatic pressing on microstructure and mechanical properties of second generation single crystal superalloy DD6[J].Journal of Materials Engineering,2016,44(10):60-67.
[16]LIBURDY J,LOWDEN P,NAGY D,et al.Practical experience with the development of superalloy rejuvenation[C]//Proceedings of Asme Turbo Expo:Power for Land,Sea,&Air.Orlando:International Gas Turbine Institute,2009:819-827.
[17]MCLEAN M,TIPLER H R.Assessment of damage accumulation and property regeneration by hot isostatic pressing and heat treatment of laboratory-tested and service exposed IN738LC[C]//Proceedings of Superalloys.Warrendale:The Metallurgical Society,1984:73-82.
[18]KOUL A K,IMMARIGEON J P,CASTILLO R,et al.Rejuvenation of service-exposed in 738 turbine blades[C]//Proceedings of Superalloys.Pennsylvania:The Minerals,Metals&Materials Society,1988:755-764.
[19]ZHANG J,ZHENG Y R,FENG Q.Study on rejuvenation heat treatment of a directionally-solidified suepralloy DZ125 damaged by creep[J].Acta Metallurgica Sinica,2016,52(6):717-726.
[20]HEN H,DONG J X,ZHANG M C.Effect of heat treatment process on microstructure of cast superalloy K480[J].Transactions of Materials and Heat Treatment,2012,33(7):37-44.
[2]TAWANCY H M,Al-HADHRAMI L M.Comparative performance of turbine blades used in power generation:damage vs.microstructure and superalloy composition selected for the application[J].Engineering Failure Analysis,2014,46(6):76-91.
[3]TARAFDER M,SUJAT M,RANGANATH V R,et al.Microstructural damage evaluation in Ni-based superalloy gas turbine blades by fractal analysis[J].Procedia Engineering,2013,55:289-294.
[4]BLACHNIO J,KULASZKA A,ZIETARA M,et al.Microstructure analysis in the creep process of a gas turbine blade of the turbine engine[J].Combustion Engines,2016,165(2):41-45.
[5]JAMES A.A review of rejuvenation process for nickel base superalloys[J].Materials Science and Technology,2013,17(5):481-486.
[6]LVOVA E.A comparison of aging kinetics of new and rejuvenated conventionally cast GTD-111 gas turbine blades[J].Journal of Materials Engineering and Performance,2007,16(2):254-264.
[7]HOSSEINI S S,NATEGH S,EKRAMI A A.Microstructural evolution in damaged IN738LC alloy during various steps of rejuvenation heat treatments[J].Journal of Alloys and Compounds,2012,512(1):340-350.
[8]MIGLIETTI W M,CURTIS R,HELM J.Rejuvenation heat treatments and their role in the repair of IN738turbine components[C]//Proceedings of Asme Turbo Expo:Power for Land,Sea,&Air.Amsterdam:International Gas Turbine Institute,2002:1197-1212.
[9]WANGYAO P,POLSILAPA S,NISARATANAPORN E.The applicaiton of hot isostatic pressing processing to rejuvenate serviced cast superalloy turbine blades[J].Acta Metallurgica Slovaca,2005,11(2):196-206.
[10]WANGYAO P,KRONGTONG V,HOMKRAJAI W,et al.Comparing rejuvenated microstructures after HIPprocess and different heat treatments in cast nickel base superalloys,IN-738 and GTD-111 after long-term service[J].Acta Metallurgica Slovaca,2006,12(1):23-32.
[11]ZHOU Y,ZHANG Z,ZHAO Z H,et al.Effects of HIPtemperature on the microstructural evolution and property restoration of a Ni-based superalloy[J].Journal of Materials Engineering and Performance,2013,22(1):215-222.
[12]ITO A,KAGIYA Y,WATANABE A.Recovery of material properties in service-degraded gas turbine blades[C]//Proceedings of the International Gas Turbine Congress.Tokyo:The Gas Turbine Society of Japan,2003:1-8.
[13]KIM H I,PARK H S,KOO J M,et al.Microstructural investigation of GTD 111DS materials in the heat treatment conditions[J].Journal of Mechanical Science and Technology,2012,26(7):2019-2022.
[14]RUTTERT B,BURGER D,RONCERY L M,et al.Rejuvenation of creep resistance of a Ni-base single-crystal superalloy by hot isostatic pressing[J].Materials&Design,2017,134:418-425.
[15]GUO H M,ZHAO Y S,ZHENG S,et al.Effect of hot-isostatic pressing on microstructure and mechanical properties of second generation single crystal superalloy DD6[J].Journal of Materials Engineering,2016,44(10):60-67.
[16]LIBURDY J,LOWDEN P,NAGY D,et al.Practical experience with the development of superalloy rejuvenation[C]//Proceedings of Asme Turbo Expo:Power for Land,Sea,&Air.Orlando:International Gas Turbine Institute,2009:819-827.
[17]MCLEAN M,TIPLER H R.Assessment of damage accumulation and property regeneration by hot isostatic pressing and heat treatment of laboratory-tested and service exposed IN738LC[C]//Proceedings of Superalloys.Warrendale:The Metallurgical Society,1984:73-82.
[18]KOUL A K,IMMARIGEON J P,CASTILLO R,et al.Rejuvenation of service-exposed in 738 turbine blades[C]//Proceedings of Superalloys.Pennsylvania:The Minerals,Metals&Materials Society,1988:755-764.
[19]ZHANG J,ZHENG Y R,FENG Q.Study on rejuvenation heat treatment of a directionally-solidified suepralloy DZ125 damaged by creep[J].Acta Metallurgica Sinica,2016,52(6):717-726.
[20]HEN H,DONG J X,ZHANG M C.Effect of heat treatment process on microstructure of cast superalloy K480[J].Transactions of Materials and Heat Treatment,2012,33(7):37-44.