航空发动机限寿件概率失效风险评估的等效应力转化
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摘要
提出一种从整个飞行循环出发并基于全局的限寿件等效应力转化方法,将转化后的等效应力作为概率失效风险评估的输入条件,从而获得更为精确的失效风险结果。首先通过流固耦合数值模拟获得限寿件在整个飞行循环的瞬态应力,然后基于雨流计数法及线性累计损伤理论编制转换程序,将限寿件模型全部节点上的瞬态应力转化为等效应力,最后作为概率失效风险分析流程的输入条件确定寿命期内的概率失效风险。相同飞行循环条件下,与基于局部最大应力的转化方法相比,全局等效应力转化方法获得的失效风险更低。该方法的提出,为我国民机型号概率失效风险评估时作为关键输入数据应力的确定给出了定量参考,有力支撑了适航取证。
An equivalent stress transformation method which based on aero-engine life-limited parts during the whole flight cycle is presented. In the method, equivalent stress is used as input conditions of failure probability risk assessment to obtain results that are more accurate. Firstly, the transient stress of life-limited parts during whole flight cycle is numerically simulated using fluid-structure interaction. A program which based on rain-flow method and linear damage accumulation theory is then applied to transfer the transient stress of nodes of life-limited parts into equivalent stress. Finally, the equivalent stress is used as input for probability risk assessment to determine failure probability risk in certain life period. Under the same flight cycle conditions, the failure risk obtained by the global transformation method of equivalent stress decreased compared with the results from the transformation method based on local maximum stress.These results can support the airworthiness forensics of aero-engine. This method can provide quantitative reference for critical input data like stress to support airworthiness certification when civil engine is under failure probability probabilistic risk assessment.
An equivalent stress transformation method which based on aero-engine life-limited parts during the whole flight cycle is presented. In the method, equivalent stress is used as input conditions of failure probability risk assessment to obtain results that are more accurate. Firstly, the transient stress of life-limited parts during whole flight cycle is numerically simulated using fluid-structure interaction. A program which based on rain-flow method and linear damage accumulation theory is then applied to transfer the transient stress of nodes of life-limited parts into equivalent stress. Finally, the equivalent stress is used as input for probability risk assessment to determine failure probability risk in certain life period. Under the same flight cycle conditions, the failure risk obtained by the global transformation method of equivalent stress decreased compared with the results from the transformation method based on local maximum stress.These results can support the airworthiness forensics of aero-engine. This method can provide quantitative reference for critical input data like stress to support airworthiness certification when civil engine is under failure probability probabilistic risk assessment.
引文
[1]Advisory Circular 33.70-1,Guidance material for aircraft engine life-limited parts requirements[S].
[2]CFR14part 33,Airworthiness standards:aircraft engines[S].
[3]Leverant G R,Littlefield D L,McClung R C,et al.Probabilistic approach to aircraft turbine rotor material design[R].ASME 97-GT-22,1997.
[4]McClung R C.Fracture mechanics analysis in DARWIN[C]//.4th Annual FAA/USAF Workshop,Application of Probabilistic Methods to Gas Turbine Engines.1999.
[5]Momin F N,Millwater H R,Osborn R W,et al.A non-intrusive method to add finite element-based random variables to a probabilistic design code[J].Finite Elements in Analysis and Design,2010,46(3):280-287.
[6]Wu Y T,Enright M P,Millwater H R,et al.Probabilistic methods for design assessment of reliability with inspection[R].AIAA 2000-1510,2000.
[7]丁水汀,张弓,蔚夺魁,等.航空发动机适航概率风险评估方法研究综述[J].航空动力学报,2011,26(7):1141-1151.
[8]赵合阳,白广忱,王科.涡轮盘低循环疲劳寿命概率分析[J].航空发动机,2009,35(1):53-56.
[9]杜少辉,洪杰,谢里阳.航空发动机断裂关键件失效率分析[J].北京航空航天大学学报,2009,35(4):464-467.
[10]Advisory Circular 33.14-1,Damage tolerance for high energy turbine engine rotors[S].
[11]Zhang G,Ding S T.Safety analysis of flow parameters in a rotor-stator cavity[J].Chinese Journal of Aeronautic,2012,17(6):831-838.
[12]杨宝峰.涡轮盘概率损伤容限评估方法研究[D].北京:北京航空航天大学,2014.
[13]刘志远,郑源.ANSYS-CFX单向流固耦合分析的方法[J].水利水电工程设计,2009,28(2):29-31.
[14]付德斌.旋转盘应力水平与温度分布的关联分析[J].航空动力学报,2008,23(4):623-628.
[15]Zagrodzki P.Numerical analysis of temperature fields and thermal stresses in the friction discs of a multidisc wet clutch[J].Wear,1985,101(3):255-271.
[16]《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[K].北京:航空工业出版社,1984.
[17]Soo S L.Laminar flow over an enclosed rotating disc[J].Trans.ASME,1958,80:287-296.
[18]叶先磊,史亚杰.ANSYS工程分析软件应用实例[M].北京:清华大学出版社,2003.
[19]张靖周,吉洪湖,王锁芳.具有径向进出流的转-静盘腔流动与换热的数值研究[J].工程热物理学报,2001,22(S1):137-140.
[20]郑玉卿,钟丰平,柯和继.基于ANSYS的减温器热固耦合应力仿真[J].计算机辅助工程,2016,(1):1-5.
[21]姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003.
[22]高镇同,熊峻江.疲劳可靠性[M].北京:北京航空航天大学出版社,2000.
[23]杨兴宇,阎晓军,赵福星,等.某型航空发动机涡轮盘低循环疲劳寿命分析[J].机械强度,2004,26(S):229-233.
[24]Leverant G R,McClung R C,Wu Y T,et al.Turbine rotor material design[R].DOT/FAA/AR-00/64,2000.
[25]ASTME 1049-85-1997,Standard practices for cycle counting in fatigue analysis[S].
[26]周俊,童小燕.雨流计数的快速实现方法[J].科学技术与工程,2008,8(13):3544-3548.
[27]张亚军.S-N疲劳曲线的数学表达式处理方法探讨[J].理化检验--物理分册,2007,43(11):563-565.
[28]张弓.航空发动机涡轮盘腔多场耦合危险机理研究[D].北京:北京航空航天大学,2013.
[29]Robert C P,Casella G.Monte Carlo statistical methods[M].New York:Springer Verlag,2004.
[30]Newman J C,Raju I S.Stress-intensity factor equations for cracks in three-dimensional finite bodies[R].NASATM-83200,1981.
[31]Newman J C,Raju I S.Stress-intensity factor equations for cracks in three-dimensional finite bodies subjected to tension and bending loads[R].NASA TM-85973,1984.
[2]CFR14part 33,Airworthiness standards:aircraft engines[S].
[3]Leverant G R,Littlefield D L,McClung R C,et al.Probabilistic approach to aircraft turbine rotor material design[R].ASME 97-GT-22,1997.
[4]McClung R C.Fracture mechanics analysis in DARWIN[C]//.4th Annual FAA/USAF Workshop,Application of Probabilistic Methods to Gas Turbine Engines.1999.
[5]Momin F N,Millwater H R,Osborn R W,et al.A non-intrusive method to add finite element-based random variables to a probabilistic design code[J].Finite Elements in Analysis and Design,2010,46(3):280-287.
[6]Wu Y T,Enright M P,Millwater H R,et al.Probabilistic methods for design assessment of reliability with inspection[R].AIAA 2000-1510,2000.
[7]丁水汀,张弓,蔚夺魁,等.航空发动机适航概率风险评估方法研究综述[J].航空动力学报,2011,26(7):1141-1151.
[8]赵合阳,白广忱,王科.涡轮盘低循环疲劳寿命概率分析[J].航空发动机,2009,35(1):53-56.
[9]杜少辉,洪杰,谢里阳.航空发动机断裂关键件失效率分析[J].北京航空航天大学学报,2009,35(4):464-467.
[10]Advisory Circular 33.14-1,Damage tolerance for high energy turbine engine rotors[S].
[11]Zhang G,Ding S T.Safety analysis of flow parameters in a rotor-stator cavity[J].Chinese Journal of Aeronautic,2012,17(6):831-838.
[12]杨宝峰.涡轮盘概率损伤容限评估方法研究[D].北京:北京航空航天大学,2014.
[13]刘志远,郑源.ANSYS-CFX单向流固耦合分析的方法[J].水利水电工程设计,2009,28(2):29-31.
[14]付德斌.旋转盘应力水平与温度分布的关联分析[J].航空动力学报,2008,23(4):623-628.
[15]Zagrodzki P.Numerical analysis of temperature fields and thermal stresses in the friction discs of a multidisc wet clutch[J].Wear,1985,101(3):255-271.
[16]《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[K].北京:航空工业出版社,1984.
[17]Soo S L.Laminar flow over an enclosed rotating disc[J].Trans.ASME,1958,80:287-296.
[18]叶先磊,史亚杰.ANSYS工程分析软件应用实例[M].北京:清华大学出版社,2003.
[19]张靖周,吉洪湖,王锁芳.具有径向进出流的转-静盘腔流动与换热的数值研究[J].工程热物理学报,2001,22(S1):137-140.
[20]郑玉卿,钟丰平,柯和继.基于ANSYS的减温器热固耦合应力仿真[J].计算机辅助工程,2016,(1):1-5.
[21]姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003.
[22]高镇同,熊峻江.疲劳可靠性[M].北京:北京航空航天大学出版社,2000.
[23]杨兴宇,阎晓军,赵福星,等.某型航空发动机涡轮盘低循环疲劳寿命分析[J].机械强度,2004,26(S):229-233.
[24]Leverant G R,McClung R C,Wu Y T,et al.Turbine rotor material design[R].DOT/FAA/AR-00/64,2000.
[25]ASTME 1049-85-1997,Standard practices for cycle counting in fatigue analysis[S].
[26]周俊,童小燕.雨流计数的快速实现方法[J].科学技术与工程,2008,8(13):3544-3548.
[27]张亚军.S-N疲劳曲线的数学表达式处理方法探讨[J].理化检验--物理分册,2007,43(11):563-565.
[28]张弓.航空发动机涡轮盘腔多场耦合危险机理研究[D].北京:北京航空航天大学,2013.
[29]Robert C P,Casella G.Monte Carlo statistical methods[M].New York:Springer Verlag,2004.
[30]Newman J C,Raju I S.Stress-intensity factor equations for cracks in three-dimensional finite bodies[R].NASATM-83200,1981.
[31]Newman J C,Raju I S.Stress-intensity factor equations for cracks in three-dimensional finite bodies subjected to tension and bending loads[R].NASA TM-85973,1984.