In-service subsurface fatigued air-engine blades

摘要：

　　The subsurface cracking of in-service compressor vane and turbine rotor blades of the Al-based alloy VD-17 and superalloy GS6K,respectively,was considered.Performed fractographic investigations have shown subsurface crack origination in Very-High-Cycle-Fatigue regime.In vane-blades crack origination was subsurface,inspite of corrosion pittings by the blade surface,because lifetime limit was reached.In superalloy GS6K fatigue cracking took place because of blades resonance under influenced gas stream.Both situations of blades cracking are discussed with crack growth period and stress equivalent estimations,and recommendations to continue aircrafts airworthiness were done based on introducing periodical non-destructive inspections for in-service blades.

关键词： engine blades subsurface very-high-cycle-fatigue fractography crack growth stress level

作者: A.A.Shanyavskiy

作者单位: State Centre for Flights Safety,Airport Sheremetievo-1,PO Box 54,Moscow region,Chimkinskaiy State,141426,Russia,

会议类型: 国际会议

会议名称: International Conference on Airworthiness & Fatigue -7th ICSAELS Series Conference(大飞机安全性能与疲劳国际会议)

会议地点: 北京

会议语种:英文

页码: 9-17

在线出版日期: 2013-03-24（万方平台首次上网日期，不代表论文的发表时间）