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首页> 外文会议>The Third International Symposium on Fretting Fatigue: Advances in Basic Understanding and Applications; May 15-18, 2001; Nagaoka, Japan >Evaluating Fatigue Life of Compressor Dovetails by Using Stress Singularity Parameters at the Contact Edge
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Evaluating Fatigue Life of Compressor Dovetails by Using Stress Singularity Parameters at the Contact Edge

机译：通过在接触边缘使用应力奇异性参数评估压缩机燕尾槽的疲劳寿命

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摘要

Fretting fatigue life of compressor dovetail for gas turbine was investigated using stress singularity theory. It is found that the crack initiation of fretting fatigue between blade dovetail and wheel dovetail occurs at the contact edge of blade dovetail. The parameters of stress singularity obtained from maximum principal stress distribution are capable to evaluate the fretting fatigue strength with the cyclic load having a constant angle against the contact surface under a variable contact pressure. The ratio of between the intensity range of stress singularity and the critical intensity range of stress singularity, Δ H 1/ Δ Hc, is an effective parameter to predict the fretting fatigue life of compressor dovetail.
机译：利用应力奇异性理论研究了燃气轮机压缩机燕尾槽的微动疲劳寿命。发现在叶片燕尾和轮燕尾之间的微动疲劳裂纹的萌生发生在叶片燕尾的接触边缘。从最大主应力分布获得的应力奇异性参数能够评估在可变接触压力下相对于接触表面具有恒定角度的循环载荷下的微动疲劳强度。应力奇异性的强度范围与应力奇异性的临界强度范围之比ΔH 1 /ΔHc是预测压缩机燕尾微动疲劳寿命的有效参数。

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