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材料工程  2016, Vol. 44 Issue (6): 84-91    DOI: 10.11868/j.issn.1001-4381.2016.06.013
  测试与表征 本期目录 | 过刊浏览 | 高级检索 |
GH4033涡轮叶片服役1600h后的显微组织及力学性能评价
付超1, 冯微2, 童锦艳1, 郑运荣1, 冯强1
1. 北京科技大学 新金属材料国家重点实验室, 北京 100083;
2. 北京航空材料研究院 熔铸中心, 北京 100095
Evaluation of Microstructure and Property of a Turbine Blade Made of GH4033 Alloy After Service for 1600h
FU Chao1, FENG Wei2, TONG Jin-yan1, ZHENG Yun-rong1, FENG Qiang1
1. State Key Laboratory for Advanced Metals and Materials, University of Science and Technology Beijing, Beijing 100083, China;
2. Melting and Casting Center, Beijing Institute of Aeronautical Materials, Beijing 100095, China
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摘要 航空发动机涡轮叶片服役过程中将产生组织退化和性能降低,从而威胁其服役安全。已有研究中,对长时服役后的叶片组织退化和性能损伤的评价研究较少。本研究对服役1600h后的GH4033合金二级涡轮叶片进行金相解剖分析和物理化学相分析;同时观察并量化表征该二级涡轮叶片各部位晶粒组织,γ+γ'基体组织和晶界碳化物,测量不同部位的维氏硬度和持久性能,分析其组织退化与性能损伤规律。结果表明:服役后叶片各部位组织退化及性能损伤程度不明显,根据γ'相的量化表征结果推断该叶片最高服役温度应不高于700℃。叶身各部位持久性能及维氏硬度与榫头部位相当,均符合航空工业标准HB/Z 91-1985要求,因而判断该叶片仍可以继续使用。研究结果对低γ'相体积分数的变形高温合金航空发动机涡轮叶片的服役安全评价具有指导意义。
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付超
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郑运荣
冯强
关键词 GH4033合金涡轮叶片服役评价显微组织持久性能    
Abstract:The microstructure and property degradation of turbine blades in aircraft engines during service would finally pose threat to service safety. But report on systematic research work about microstructure and property degradation of serviced turbine blades is limited. In this paper, the 2nd stage turbine blade made of wrought Ni-based superalloy GH4033 was taken from an aircraft engine and investigated by metallographic analysis and physical and chemical phase analysis after service exposure for about 1600 engine operating hours (EOH). Microstructural features including grain microstructure, γ+γ' matrix and grain boundary (GB) carbides in different locations of the serviced blade were observed and quantitatively characterized. Vickers hardness and stress rupture tests were also conducted. The microstructure characterization indicates that the degradation in grain size, γ' precipitates and GB carbides is rarely observed in the airfoil. The service temperature is estimated to be lower than 700℃ based on the coarsen of γ' phase. The Vickers hardness and rupture lives of different locations in this blade are similar to those in the shank and met the requirement of Chinese Aeronautical Industry Standard HB/Z 91-1985. Therefore, it is suggested that the service exposure of this blade can be continuously prolonged. This study would be helpful for the evaluation of turbine blade made of wrought superalloys containing low volume fraction of γ' precipitates.
Key wordsGH4033 alloy    turbine blade    service evaluation    microstructure    stress rupture property
收稿日期: 2015-09-02      出版日期: 2016-06-13
中图分类号:  TG132.3+2  
通讯作者: 冯强(1969-),男,教授,主要从事高温结构材料相关研究工作,联系地址: 北京市海淀区学院路30号北京科技大学新金属材料国家重点实验室(100083),E-mail:qfeng@skl.ustb.edu.cn     E-mail: qfeng@skl.ustb.edu.cn
引用本文:   
付超, 冯微, 童锦艳, 郑运荣, 冯强. GH4033涡轮叶片服役1600h后的显微组织及力学性能评价[J]. 材料工程, 2016, 44(6): 84-91.
FU Chao, FENG Wei, TONG Jin-yan, ZHENG Yun-rong, FENG Qiang. Evaluation of Microstructure and Property of a Turbine Blade Made of GH4033 Alloy After Service for 1600h. Journal of Materials Engineering, 2016, 44(6): 84-91.
链接本文:  
http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2016.06.013      或      http://jme.biam.ac.cn/CN/Y2016/V44/I6/84
[1] SIMS C T, STOLOFF N S,HAGEL W C. Superalloys II[M]. New York:John Wiley and Sons, 1987.
[2] 齐欢. Inconel 718(GH4169)高温合金的发展与工艺[J]. 材料工程, 2012,(8):92-100. QI H. Review of Inconel 718 alloy:its history, properties, processing and developing Substitutes[J]. Journal of Materials Engineering, 2012,(8):92-100.
[3] CASTILLO R, KOUL A K, IMMARIGEON J P. The effect of service exposure on the creep properties of cast IN-738LC subjected to low stress high temperature creep conditions[C]//Superalloys.[S.l.]:[s.n.], 1988.
[4] OHTA Y, YOSHIZAWA H, NAKAGAWA Y G. Microstructural changes in a Ni-base superalloy during service[J]. Scripta Metallurgica, 1989, 23(9):1609-1614.
[5] 冯强, 童锦艳, 郑运荣,等. 燃气涡轮叶片的服役损伤与修复[J]. 中国材料进展, 2012, 31(12):21-34. FENG Q, TONG J Y, ZHENG Y R,et al. Service induced degradation and rejuvenation of gas turbine blades[J]. Materials China, 2012, 31(12):21-34.
[6] 童锦艳, 冯微, 付超, 等. GH4033合金短时超温后的显微组织损伤及其对力学性能的影响[J]. 金属学报, 2015, 51(10):1242-1252. TONG J Y, FENG W, FU C,et al. Effects of microstructural degradation caused by overheating on mechanical properties of turbine blade[J]. Acta Metallurgica Sinica, 2015, 51(10):1242-1252.
[7] 高原. 高温合金生产新工艺新技术与金相图谱及常用数据速用速查手册[M]. 北京:中国科技文化出版社, 2006.
[8] XU Y, JIN Q, XIAO X,et al. Strengthening mechanisms of carbon in modified nickel-based superalloy Nimonic 80A[J]. Materials Science and Engineering:A, 2011, 528(13):4600-4607.
[9] VOICE W E, FAULKNER R G. Carbide stability in Nimonic 80a alloy[J]. Metallurgical Transactions:A, 1985, 16(4):511-520.
[10] HB/Z 91-1985, 航空用高温合金涡轮叶片模锻件[S].
[11] TONG J Y, DING X F, WANG M L,et al. Evaluation of a serviced turbine blade made of GH4033 wrought superalloy[J]. Materials Science and Engineering:A, 2014, 618:605-613.
[12] GB/T 6394-2002,金属平均晶粒度测定方法[S].
[13] GB/T 14999.4-1994, 高温合金显微组织实验法[S].
[14] KOUL A K, ZHOU X, FULEKI D,et al. Importance of physics based prognosis for improving turbine reliability[A].Proc 16th Canadian Symposium of the Industrial Applications of Gas Turbines[C]. Canada:IAGT, 2005.
[15] MIURA N, NAKATA K, MIYAZAKI M,et al. Morphology of γ' precipitates in second stage high pressure turbine blade of single crystal nickel-based superalloy after service[J]. Materials Science Forum, 2010, 638-642:2291-2296.
[16] TONG J, DING X F, WANG M L,et al. Assessment of service induced degradation of microstructure and properties in turbine blades made of GH4037 alloy[J]. Journal of Alloys and Compounds, 2016, 657:777-786.
[17] 张俊善. 材料的高温变形与断裂[M]. 北京:科学出版社, 2007.
[18] 郭建亭. 高温合金材料学(下册):高温合金材料与工程应用[M].北京:科学出版社, 2010.
[19] 姚志浩, 董建新, 张麦仓, 等. GH864合金显微组织与力学性能的关联性[J]. 稀有金属材料与工程, 2010, 39:1565-1569. YAO Z H, DONG J X, ZHANG M C,et al. Relationships between microstructure and properties for GH864 superalloy[J]. Rare Metal Material and Engineering, 2010, 39:1565-1569.
[20] 谭毅, 廖娇, 李佳艳, 等. 电子束熔炼Inconel 740合金不同热处理状态下的组织演变与显微硬度[J]. 材料工程, 2015, 43(4):19-24. TAN Y, LIAO J, LI J Y,et al. Microstructure evolution and microstructure of Inconel 740 alloy in different heat-treatment condition prepared by electron beam melting[J]. Journal of Materials Engineering, 2015, 43(4):19-24.
[21] 郭建亭. 高温合金材料学(上)应用基础理论[M].北京:科学出版社, 2008.
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