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首页> 美国政府科技报告 >Improved Damage Tolerance of Ti-6Al-4V Aero Engine Blades and Vanes Using Residual Compression by Design
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Improved Damage Tolerance of Ti-6Al-4V Aero Engine Blades and Vanes Using Residual Compression by Design

机译：利用设计的残余压缩改善Ti-6al-4V航空发动机叶片和叶片的损伤容限

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摘要

The deep stable layer of compressive residual stress produced by low plasticity burnishing (LPB) has been demonstrated in laboratory testing to improve damage tolerance in engine alloys IN718, Ti-6Al-4V, Ti-6-2-4-6, and 17- 4PH. This paper describes the fatigue and FOD tolerance benefits afforded by LPB treatment of a Ti-6Al-4V first stage fan blade and vane. FOD sensitive blades and vanes removed from fielded engines were LPB processed to protect the leading edge of the blade and the trailing edge of the vane. Both components were fatigue tested in cantilever bending mode at R>0 using specially designed test fixtures. FOD was simulated with machined notches for the blade and electrical discharge machined (EDM) notches for the vane. Residual stress and cold work distributions were measured using x-ray diffraction mapping techniques.

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