IMPROVED PROCESS/PROPERTY/DESIGN INTEGRATION OF TITANIUM BASED AEROENGINE COMPONENTS

摘要

Improved fatigue understanding of compressor blade components is essential. Direct comparison between simple specimen and component tests have revealed marked differences in fatigue life. Therefore, Rolls-Royce are developing a new LCF/HCF rig using a testpiece that will contain representative compressor blade features. The ability to test realistic testpieces under appropriate stress regimes is essential. Development of suitable lifing methodologies will mean both a reduction of in-service failures and blade overdesign. This will result in a huge potential cost saving to the company.