The　dovetail　joint　interfaces　in　aero-engine　are　susceptible　to　fretting　wear,　which　can　result　in　premature　failure.　Based　on　two-dimensional　(2D)　blade/disk　contact　finite　element　(FE)　model　and　the　energy　model,　an　original　substrate-debris-glaze　conversion　method　is　proposed　and　validated　to　predict　the　presence　of　a　glaze　layer　at　high　temperatures　in　fretting　wear.　The　present　work　investigates　the　effects　of　bottom　angle,　friction　coefficient,　centrifugal　force　and　temperature　on　fretting　wear　of　the　dovetail　joint.　The　results　indicate　that　fretting　wear　predominantly　occurs　near　the　edges　of　the　contact　areas.　Furthermore,　the　formation　of　glaze　layer　at　high　temperatures　leads　to　a　significant　reduction　in　wear　depth,　ranging　from　50%　to　93%,　compared　to　low　temperatures　without　glaze　layer.　©　2024