镍基单晶高温合金DD6气膜孔热机械疲劳试验

蒋康河; 陈竞炜; 荆甫雷; 张斌; 胡殿印; 王荣桥

doi:10.13224/j.cnki.jasp.2019.05.003

镍基单晶高温合金DD6气膜孔热机械疲劳试验

doi: 10.13224/j.cnki.jasp.2019.05.003

1.
中国航空发动机集团有限公司湖南动力机械研究所，湖南株洲 412002
2.
中国航空发动机集团有限公司中国航空发动机研究院，北京 101304
3.
北京航空航天大学能源与动力工程学院，北京 100191

基金项目: 航空动力基金（6141B090544）

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出版历程
- 收稿日期: 2018-07-18
- 刊出日期: 2019-05-28

Thermomechanical fatigue on the nickel based single crystal superalloy DD6 with film cooling hole

摘要

摘要: 涡轮冷却叶片气膜孔边存在大应力梯度，且服役时承受交变的机械载荷和热载荷，热机械疲劳（TMF）是其主要失效模式。通过开展带气膜孔和不带气膜孔的薄壁圆管试件TMF试验研究了气膜孔对镍基单晶高温合金TMF寿命的影响。结果表明最大循环应力在300~500 MPa应力范围内，循环应力幅值与镍基单晶高温合金TMF寿命呈现良好的对数线性关系，且气膜孔导致镍基单晶高温合金TMF寿命下降可达82.5%。继而完成了横向取向分别为〈010〉、〈110〉方向的气膜孔模拟件试验，结果表明气膜孔取向为〈110〉时寿命最短，仅为〈010〉取向的40.0%。最后开展了不同制孔工艺下的气膜孔模拟件试验，结果表明激光制孔气膜孔模拟试件寿命仅为电液束制孔气膜孔模拟试件的54.0%。气膜孔模拟件断口分析表明：TMF裂纹均萌生于气膜孔边，源区氧化严重；裂纹沿着大致与气膜孔边垂直的方向扩展。
- 镍基单晶高温合金DD6 /
- 气膜孔 /
- 热机械疲劳 /
- 横向取向 /
- 制孔工艺
Abstract: Turbine blades are subjected to thermal loads and mechanical loads simultaneously occurring during operation. Thermomechanical fatigue (TMF) is a major life-limiting factor for turbine blades. Film cooling holes within the blade introduced substantial stress concentration, which could dramatically reduce the lifetime. For quantification purposes, both smooth tubular specimens and notched specimens were utilized to perform TMF experiments. Results indicated that stress and fatigue life were in a good logarithmic linear correlation when the maximum stress changes within the range of 300-500 MPa and the hole could reduce the TMF life by 82.5%. Notched specimens with 〈010〉 and 〈110〉 oriented hole were tested respectively. It was found that the hole in 〈110〉 orientation had the weakest anti-TMF ability, since its life was only 40.0% of the 〈010〉 oriented notched specimen. The effect of drilling process was also studied. The results revealed that the life of notched specimen drilled by laser was 54.0% of the notched specimen drilled by electro-streaming drilling. The crack morphology demonstrated that TMF crack initiated from the film cooling hole edge which was severely oxidized and the crack propagated along the direction perpendicular to the edge of the hole.
- nickel based single crystal superalloy DD6 /
- film cooling hole /
- thermomechanical fatigue /
- secondary orientation /
- drilling process

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参考文献(22)

[1]	REED R C.The superalloys:fundamentals and applications［M］.New York:Cambridge University Press,2006.
[2]	胡壮麒,刘丽荣,金涛,等.镍基单晶高温合金的发展［J］.航空发动机,2005,31(3):1-7.HU Zhuangqi,LIU Lirong,JIN Tao,et al.Development of the Ni-base single crystal superalloys［J］.Aeroengine,2005,31(3):1-7.(in Chinese)
[3]	WANG Rongqiao,JIANG Kanghehe,JING Fulei,et al.Thermomechanical fatigue failure investigation on a single crystal nickel superalloy turbine blade［J］.Engineering Failure Analysis,2016,66(8):284-295.
[4]	HAN Guoming,YU Jinjiang,SUN Xiaofeng,et al.Thermo-mechanical fatigue behavior of single crystal nickel-based superalloy［J］.Material Science and Engineering A,2011,528(19/20):6217-6224.
[5]	KERSEY R K,STAROSELSKY A,DUDZINSKI D C,et al.Thermomechanical fatigue crack growth from laser drilled holes in single crystal material［J］.International Journal of Fatigue,2013,55:183-193.
[6]	ABDULLAHI O A,SAMIR E,PANAGIOTIS L,et al.Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model［J］.International Journal of Fatigue,2014,61:160-169.
[7]	LEIDERMARK D.Evaluation of thermomechanical fatigue crack initiation in a single-crystal superalloy［J］.Studies in European Cinema,2015,11(3):155-169.
[8]	ZHANG W J.Thermal mechanical fatigue of single crystal superalloys:achievements and challenges［J］.Materials Science and Engineering A,2016,650:389-395.
[9]	卢绪平,温志勋,岳珠峰,等.镍基单晶气膜孔模拟试样的低周疲劳断裂机理［J］.稀有金属材料与工程,2015,44(5):1173-1176.LU Xuping,WEN Zhixun,YUE Zhufeng,et al.Low cycle fatigue fracture mechanism of a modeling specimen with cooling film hole of DD6 single crystal superalloy［J］.Rare Metal Materials and Engineering,2015,44(5):1173-1176.(in Chinese)
[10]	胡春燕,徐元铭,刘新灵,等.DD6单晶合金气膜孔薄壁平板高温持久性能［J］.失效分析与预防,2017,12(1):38-42.HU Chunyan,XU Yuanming,LIU Xinling,et al.Stress rupture behavior of modeling specimen with cooling holes of single crystal superalloy DD6［J］.Failure Analysis and Prevention,2017,12(1):38-42.(in Chinese)
[11]	何爱杰,李世峰,罗秋生,等.高温下DD6单晶气冷叶片模拟试样拉伸性能试验［J］.航空动力学报,2012,27(2):255-259.HE Aijie,LI Shifeng,LUO Qiusheng,et al.Experimental investigation on tension behavior of DD6 single crystal thin-walled cylindrical specimen under high temperature［J］.Journal of Aerospace Power,2012,27(2):255-259.(in Chinese)
[12]	卿华,江和甫,温卫东,等.镍基单晶合金气冷叶片模拟试样的蠕变性能研究［J］.航空动力学报,2007,22(5):773-778.QING Hua,JIANG Hefu,WEN Weidong,et al.Study on the creep behavior of model specimens of nickel based single crystal air cooled blades［J］.Journal of Aerospace Power,2007,22(5):773-778.(in Chinese)
[13]	赵新宝,高斯峰,杨初斌,等.镍基单晶高温合金晶体取向的选择及其控制［J］.中国材料进展,2013,32(1):24-38.ZHAO Xinbao,GAO Sifeng,YANG Chubin,et al.Influence of crystal orientation on microstructure and mechanical properties and its control for nickel-basesingle crystal superalloys［J］.Materials China,2013,32(1):24-38.(in Chinese)
[14]	朱海南,齐歆霞.涡轮叶片气膜孔加工技术及其发展［J］.航空制造技术,2011(13):71-74.ZHU Hainan,QI Xinxia.Development of machining technology gas holes on turbine blades［J］.Aeronautical Manufacturing Technology,2011(13):71-74.(in Chinese)
[15]	张晓兵.激光加工涡轮叶片气膜孔的现状及发展趋势［J］.应用激光,2002,22(4):227-246.ZHANG Xiaobing.The present state and perspective of laser drilling technology in turbine blades［J］.Applied Laser,2002,22(4):227-246.(in Chinese)
[16]	刘新灵,陶春虎,刘春江,等.航空发动机叶片气膜孔加工方法及其演变分析［J］.材料导报,2013,27(11):117-120.LIU Xinling,TAO Chunhu,LIU Chunjiang,et al.Investigation of processing methods and development of gas holes of engine blade［J］.Materials Reports,2013,27(11):117-120.(in Chinese)
[17]	潘志福,张明岐,傅军英,等.航空发动机高品质小孔电液束加工技术［J］.航空制造技术,2015,58(23/24):64-66.PAN Zhifu,ZHANG Mingqi,FU Junying,et al.Electro stream machining technology of high quality hole in aeroengine［J］.Aeronautical Manufacturing Technology,2015,58(23/24):64-66.(in Chinese)
[18]	《航空发动机设计用材料数据手册编委会》.航空发动机设计用材料数据手册:第四册［M］.北京:航空工业出版社,2010.
[19]	BSI Standards Publication Metallic Materials.Strain-controlled thermomechanical fatigue testing method ISO 12111:2011(E)［S］.London:BSI Publication,2011:1-36.
[20]	ASTM International.Practice for strain controlled thermomechanical fatigue testing ASTM E2368-10 Standard［S］.Pennsylvania,US:ASTM International,2010:1-10.
[21]	HHNER P,AFFELDT E,BECK T,et al.Research and development into a Eruropean code-of-practice for strain-controlled thermo-mechanical fatigue testing［J］.International Journal of Fatigue,2008,30(2):372-381.
[22]	何玉怀,张国栋,鲁原.金属材料热机械疲劳试验方法GJB 6213-2008［S］.北京:国防科学技术工业委员会,2008:1-12.