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High Cycle Fatigue Life Prediction and Reliability Analysis of Aeroengine Blades

High Cycle Fatigue Life Prediction and Reliability Analysis of Aeroengine Blades
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摘要 Based on the nonlinear continuum damage model (CDM) developed by Chaboehe, a modified model for high cycle fatigue of TC4 alloy was proposed. Unsymmetrical cycle fatigue tests were conducted on rod specimens at room temperature. Then the material parameters needed in the CDM were obtained by the fatigue tests, and the stress distribution of the specimen was calculated by FE method. Compared with the linear damage model (LDM), the dam- age results and the life prediction of the CDM show a better agreement with the test and they are more precise than the LDM. By applying the CDM developed in this study to the life prediction of aeroengine blades, it is concluded that the root is the most dangerous region of the whole blade and the shortest life is 58 211 cycles. Finally, the Cox propor- tional hazard model of survival analysis was applied to the analysis of the fatigue reliability. The Cox model takes the covariates into consideration, which include diameter, weight, mean stress and tensile strength. The result shows that the mean stress is the only factor that accelerates the fracture process. Based on the nonlinear continuum damage model(CDM) developed by Chaboche,a modified model for high cycle fatigue of TC4 alloy was proposed.Unsymmetrical cycle fatigue tests were conducted on rod specimens at room temperature.Then the material parameters needed in the CDM were obtained by the fatigue tests,and the stress distribution of the specimen was calculated by FE method.Compared with the linear damage model(LDM),the damage results and the life prediction of the CDM show a better agreement with the test and they are more precise than the LDM.By applying the CDM developed in this study to the life prediction of aeroengine blades,it is concluded that the root is the most dangerous region of the whole blade and the shortest life is 58 211 cycles.Finally,the Cox proportional hazard model of survival analysis was applied to the analysis of the fatigue reliability.The Cox model takes the covariates into consideration,which include diameter,weight,mean stress and tensile strength.The result shows that the mean stress is the only factor that accelerates the fracture process.
出处 《Transactions of Tianjin University》 EI CAS 2012年第6期456-464,共9页 天津大学学报(英文版)
基金 Supported by National Natural Science Foundation of China(No.60879002) Key Technologies R and D Program of Tianjin (No.10ZCKFGX03800)
关键词 life prediction RELIABILITY continuum damage model survival analysis Cox proportional hazard model aeroengine blade 航空发动机叶片 疲劳可靠性分析 疲劳寿命预测 循环疲劳试验 非线性连续 损伤模型 清洁发展机制 风险模型
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