APU二级涡轮叶片疲劳寿命计算与分析
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摘要
为了定位二级涡轮叶片疲劳危险部位,采用CATIA、ANSYS Workbench和CFX软件对二级涡轮叶片进行建模、流场仿真,利用Newton迭代法和Manson-Coffin公式对叶片流-热-固多场耦合等效应力应变进行计算,预测了叶片疲劳寿命,确定了叶片疲劳危险部位,然后通过Fatigue Tool软件仿真验证了这一局部应力应变预测方法所得结果的合理性与可行性。这一预测方法为后期对叶片的实验研究、设计及优化提供参考。
In order to locate the fatigue risk area of the second stage turbine blade, CATIA, ANSYS Workbench and CFX software are used to model the second stage turbine blade and simulate the flow field. The Newton iterative method and the Manson-Coffin formula are used to calculate the fluid-thermal-solid multi-field coupling equivalent stress strain. The fatigue life of the blade is predicted, and the fatigue risk area of the blade is determined. Then, the rationality and feasibility of the results obtained by the local stress-strain approach are proved by the Fatigue Tool software simulation. The prediction method provides a reference for the experimental research, design and optimization of the blade in the later period.
In order to locate the fatigue risk area of the second stage turbine blade, CATIA, ANSYS Workbench and CFX software are used to model the second stage turbine blade and simulate the flow field. The Newton iterative method and the Manson-Coffin formula are used to calculate the fluid-thermal-solid multi-field coupling equivalent stress strain. The fatigue life of the blade is predicted, and the fatigue risk area of the blade is determined. Then, the rationality and feasibility of the results obtained by the local stress-strain approach are proved by the Fatigue Tool software simulation. The prediction method provides a reference for the experimental research, design and optimization of the blade in the later period.
引文
[1] 陈龙,彭高明,罗淑洪.基于ANSYS的斗齿疲劳寿命预测[J].热加工工艺,2015,44(22):49-52.
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[3] 高振山,邓效忠,陈拂晓,等.基于局部应力应变法弧齿锥齿轮锻造模具寿命预测[J].机械传动,2013,37(12):31-34.
[4] 熊伟红,向晓东,喻青.基于局部应力应变法的桥式起重机用钢丝绳疲劳寿命估算[J].机械科学与技术,2015,34(1):47-50.
[5] 曽波.某航空发动机涡轮叶片动态可靠性建模与分析[D].成都:电子科技大学,2013.
[6] 彭立强.大型燃气轮机涡轮叶片疲劳寿命研究[D].大连:大连理工大学,2008.
[7] 王奉明,朱俊强,徐纲.基于整机试车的涡轮叶片高低循环复合疲劳试验技术[J].航空动力学报,2018,33(10):2343-2350.
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[9] 陈传尧.疲劳与断裂[M].武汉:华中科技大学出版社,2001:71-76.
[10] ZHOU J,HUANG H Z,PENG Z C.Fatigue life prediction of turbine blades based on a modified equivalent strain model[J].Journal of Mechanical Science and Technology,2017,31(9):4203-4213.
[11] 尹珩苏.航空发动机低压涡轮叶片疲劳寿命预测[D].成都:电子科技大学,2016.
[12] 蔡伟.某涡扇发动机涡轮叶片寿命计算分析[D].成都:电子科技大学,2014.
[13] 王伟政.航空高压涡轮叶片低周疲劳/蠕变研究[D].大连:大连理工大学,2018.
[14] 陈志英,王朝,周平.涡轮叶片疲劳-蠕变寿命稳健性优化方法[J],航空发动机,2017,43(4):11-16.
[15] 穆丽娟.基于临界面法的涡轮单晶叶片低周疲劳疲劳寿命预测方法研究[D].北京:中国科学院大学,2017.
[2] 杨志凌,毛丽娟.基于CAE软件风电机组齿轮疲劳寿命预测[J].计算机仿真,2015,32(2):161-169.
[3] 高振山,邓效忠,陈拂晓,等.基于局部应力应变法弧齿锥齿轮锻造模具寿命预测[J].机械传动,2013,37(12):31-34.
[4] 熊伟红,向晓东,喻青.基于局部应力应变法的桥式起重机用钢丝绳疲劳寿命估算[J].机械科学与技术,2015,34(1):47-50.
[5] 曽波.某航空发动机涡轮叶片动态可靠性建模与分析[D].成都:电子科技大学,2013.
[6] 彭立强.大型燃气轮机涡轮叶片疲劳寿命研究[D].大连:大连理工大学,2008.
[7] 王奉明,朱俊强,徐纲.基于整机试车的涡轮叶片高低循环复合疲劳试验技术[J].航空动力学报,2018,33(10):2343-2350.
[8] 姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003:117-152.
[9] 陈传尧.疲劳与断裂[M].武汉:华中科技大学出版社,2001:71-76.
[10] ZHOU J,HUANG H Z,PENG Z C.Fatigue life prediction of turbine blades based on a modified equivalent strain model[J].Journal of Mechanical Science and Technology,2017,31(9):4203-4213.
[11] 尹珩苏.航空发动机低压涡轮叶片疲劳寿命预测[D].成都:电子科技大学,2016.
[12] 蔡伟.某涡扇发动机涡轮叶片寿命计算分析[D].成都:电子科技大学,2014.
[13] 王伟政.航空高压涡轮叶片低周疲劳/蠕变研究[D].大连:大连理工大学,2018.
[14] 陈志英,王朝,周平.涡轮叶片疲劳-蠕变寿命稳健性优化方法[J],航空发动机,2017,43(4):11-16.
[15] 穆丽娟.基于临界面法的涡轮单晶叶片低周疲劳疲劳寿命预测方法研究[D].北京:中国科学院大学,2017.