基于主动热载荷管理技术的涡轮盘疲劳寿命
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摘要
为降低航空发动机涡轮盘失效风险并提高使用寿命,将主动热载荷管理技术应用于预置裂纹的涡轮盘模型,采用通用权函数法计算裂纹应力强度因子进而分析轮盘寿命,研究经主动热载荷管理的轮盘上能量分布对轮盘寿命的影响,探索轮盘上热边界载荷与寿命的关联性和变化规律,并通过有限元仿真模拟初步分析其作用机理。结果表明:主动热载荷管理技术通过优化轮盘的温度分布,可以有效地降低裂纹附近的应力,延缓裂纹的扩展,显著的提高寿命和安全性,当热边界载荷系数分别取0.05和0.10时,轮盘相应的寿命分别增加12.2%和26.1%。
In order to reduce the failure risk of turbine disk and extend its life,actively managed thermal loading method was applied to the turbine disk with pre-set crack.Meanwhile,the crack stress intensity factors were calculated by general weight function method and the life of the turbine disk was analyzed.The influence of the energy distribution based on actively managed thermal loading method on the life of the turbine disk was studied.The relationship and change trend between the thermal boundary loading and the life of the turbine disk were explored.The reason and mechanism were analyzed by finite element numerical simulation.The consequence shows that actively managed thermal loading method can effectively optimize the temperature distribution of the turbine disk,reduce the stress near thecrack,delay the expansion of the crack,and significantly improve its life and safety.When the thermal boundary loading coefficient was 0.05 and 0.10 respectively,the corresponding lives increase by 12.2% and 26.1%.
In order to reduce the failure risk of turbine disk and extend its life,actively managed thermal loading method was applied to the turbine disk with pre-set crack.Meanwhile,the crack stress intensity factors were calculated by general weight function method and the life of the turbine disk was analyzed.The influence of the energy distribution based on actively managed thermal loading method on the life of the turbine disk was studied.The relationship and change trend between the thermal boundary loading and the life of the turbine disk were explored.The reason and mechanism were analyzed by finite element numerical simulation.The consequence shows that actively managed thermal loading method can effectively optimize the temperature distribution of the turbine disk,reduce the stress near thecrack,delay the expansion of the crack,and significantly improve its life and safety.When the thermal boundary loading coefficient was 0.05 and 0.10 respectively,the corresponding lives increase by 12.2% and 26.1%.
引文
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[14]孙贺兴.变厚度轮盘应力的热边界载荷效应及应用研究[D].北京:北京航空航天大学,2015.SUN Hexing.Study and application the effect of thermal boundary loading on stress state of variable thickness disk[D].Beijing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese)
[15]WU X R,CARLSSON A J.Weight functions and stress intensity factor solutions[M].New York:Pergamum Press,1991.
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[17]SHEN G,GLINKA G.Determination of weight functions from reference stress intensity factors[J].Theoretical and Applied Fracture Mechanics,1991,15(3):237-245.
[18]SHEN G,GLINKA G.Universal features of weight functions for cracks in modeⅠ[J].Engineering Fracture Mechanics,1991,40(6):1135-1146.
[19]丁遂栋.断裂力学[M].北京:机械工业出版社,1997.
[20]US Department of Transportation,Federal Aviation Administration.Advisory circular 33.14-1:damage tolerance for high energy turbine engine rotors[R].Washington DC:FAA,AC 33.14-1,2001.
[21]北京航空材料研究所.航空发动机设计用材料数据手册[M].北京:中国航空发动机总公司,1984:1183-1185.
[2]李果.航空发动机热端部件的主动热应力控制机理研究[D].北京:北京航空航天大学,2012.LI Guo.Study on an active control thermal stresses method in heated components of areo-engine[D].Beijing:Beijing University of Aeronautics and Astronautics,2012.(in Chinese)
[3]丁水汀,王子尧,李果.变厚度涡轮盘上能量与应力分布的关联分析[J].航空动力学报,2015,30(2):341-348.DING Shuiting,WANG Ziyao,LI Guo.Correlation analysis of energy and stress distribution on variable thickness turbine disks[J].Journal of Aerospace Power,2015,30(2):341-348.(in Chinese)
[4]丁水汀,孙贺兴,李果.涡轮盘优化设计中的热边界载荷控制效果研究[J].航空动力学报,2016,31(11):2731-2737.DING Shuiting,SUN Hexing,LI Guo.Control effect study on thermal boundary loading in optimization design of turbine disk[J].Journal of Aerospace Power.2016,31(11):2731-2737.(in Chinese)
[5]WANG Ziyao,DING Shuiting,LI Guo.Failure risk control for aeroengine turbine disks based on active thermal management[J].Applied Thermal Engineering,2017,120(25):367-377.
[6]王自强,陈少华.高等断裂力学[M].北京:科学出版社,2009.
[7]BUECKNER H F.A novel principle for the computation of stress intensity factors[J].Zeitschrift Angewandte Mathematik und Mechanik,1970,50(9):529-546.
[8]RICE J.Some remarks on elastic crack-tip stress field[J].International Journal of Solids and structures,1972,8(6):751-758.
[9]张弓,周燕佩,丁水汀.面向适航要求的涡轮发动机限寿件概率失效风险评估方法[J].航空动力学报,2015,30(10):2338-2345.ZHANG Gong,ZHOU Yanpei,DING Shuiting.Probabilistic failure risk assessment method of turbine engine life limited parts for airworthiness requirements[J].Journal of Aerospace Power,2015,30(10):2338-2345.(in Chinese)
[10]LEVERANT G R,LITTLEFIELD D L,MCCLUNG R C,et al.Probabilistic approach to aircraft turbine rotor material design[R].ASME Paper 97-GT-22,1997.
[11]MCCLUNG R C.Fracture mechanics analysis in DARWIN[R].Jacksonville,Florida,US:4th Annual FAA/USAF workshop Application of Probabilistic Methods to Gas Turbine Engine,1999.
[12]MCCLUNG R C,LEE Y D,ENRIGHT M P.A new computational frame work for fatigue crack growth analysis of components[R].Ottawa,Canada:12th International Conference on Fracture,2009.
[13]李烨.过渡过程中旋转轮盘热应力演化机理研究[D].北京:北京航空航天大学,2014.LI Ye.Evolution mechanism of thermal stress in a rotating disk during a transient process[D].Beijing:Beijing University of Aeronautics and Astronautics,2014.(in Chinese)
[14]孙贺兴.变厚度轮盘应力的热边界载荷效应及应用研究[D].北京:北京航空航天大学,2015.SUN Hexing.Study and application the effect of thermal boundary loading on stress state of variable thickness disk[D].Beijing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese)
[15]WU X R,CARLSSON A J.Weight functions and stress intensity factor solutions[M].New York:Pergamum Press,1991.
[16]ZHAO W,WU X R,YAN M G.Weight function method for three dimensional crack problems:Ⅰbasic formulation and application to an embedded elliptical crackinfinite plates[J].Engineering Fracture Mechanics,1989,34(3):593-607.
[17]SHEN G,GLINKA G.Determination of weight functions from reference stress intensity factors[J].Theoretical and Applied Fracture Mechanics,1991,15(3):237-245.
[18]SHEN G,GLINKA G.Universal features of weight functions for cracks in modeⅠ[J].Engineering Fracture Mechanics,1991,40(6):1135-1146.
[19]丁遂栋.断裂力学[M].北京:机械工业出版社,1997.
[20]US Department of Transportation,Federal Aviation Administration.Advisory circular 33.14-1:damage tolerance for high energy turbine engine rotors[R].Washington DC:FAA,AC 33.14-1,2001.
[21]北京航空材料研究所.航空发动机设计用材料数据手册[M].北京:中国航空发动机总公司,1984:1183-1185.