摘要
随着航空工业的发展,对发动机特别是涡轮叶片的性能要求也越来越苛刻。目前涡轮叶片的组织主要为柱状晶或单晶,采用定向凝固技术制造。由于合金元素种类繁多、叶片形状和内腔复杂,在制造过程中叶片容易产生各种铸造缺陷,如杂晶、大/小角晶界、雀斑等,导致叶片合格率低、研发周期长、制造成本高。数值模拟技术作为一种低能耗、高效率、短周期的研究方法,能有效预测缺陷产生,优化涡轮叶片定向凝固工艺,提高成品率。介绍了高温合金涡轮叶片定向凝固模拟的物理数学模型,总结了国内外航发叶片成形过程中数值模拟技术的研究进展,并对其发展方向进行了展望。
With the development of aviation industry,the performance requirements of engine,especially turbine blades,are becoming more and more stringent.At present,the structure of turbine blade is mainly columnar crystal or single crystal.Directional solidification technology was used to manufacture turbine blade.Due to the variety of alloy elements and the complexity of blade shape and inner cavity,the blade was prone to produce various casting defects in the manufacturing process,such as impurities,large/small angle grain boundaries,freckles,which led to low qualification rate,long R&D cycle and high manufacturing cost.As a research method with low energy consumption,high efficiency and short cycle,numerical simulation technology can effectively predict the defects,optimize the directional solidification process of turbine blade and improve the yield.The physical and mathematical models for directional solidification simulation of nickel-based superalloy turbine blades were introduced.The research progress of numerical simulation technology in aeroengine blade forming process at home and abroad was summarized and its development direction was prospected.
作者
许庆彦
夏鹄翔
XU Qing-yan;XIA Hu-xiang(Key Laboratory for Advanced Materials Processing Technology(Ministry of Education),School of Materials Science and Engineering,Tsinghua University,Beijing 100084,China)
出处
《航空发动机》
北大核心
2021年第4期141-148,共8页
Aeroengine
基金
国家科技重大专项(2017-VI-0003-0073)资助。
关键词
镍基高温合金
数值模拟
定向凝固
涡轮叶片
高温蠕变
铸造缺陷
航空发动机
nickel-based superalloy
numerical simulation
directional solidification
turbine blade
high temperature creep
casting defect
aeroengine
