928 応力特異場パラメータを用いたダブテールのフレッティング疲労評価法

概要

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The fretting fatigue life of airplane engine dovetail was investigated using stress singularity theory. The crack initiation of fretting fatigue occurs at the contact edge of blade dovetail between blade dovetail and wheel dovetail. The parameters of stress singularity obtained from maximum principal stress distribution by finite element method analysis is effective to evaluate the fretting fatigue with the cyclic load having a constant angle against the contact surface under a variable contact pressure in case of titanium alloy as well as in case of steel. The ratio ΔHl/ΔHc between intensity range of stress singularity and critical intensity range of stress singularity is an useful parameter to predict the fretting fatigue life.
一般社団法人日本機械学会の論文
2002-10-10