Spin testing of high-bypass turbofan engine fan blades discovered that disk bushings at the blade attachment location frequently backed out during operation causing a deep groove to wear into the attachment tang of the blade. Their movement was the result of insufficient interference fit between the fan disk and bushing. Finite element analysis and microscopic examination of the fan blade fracture surface show that the wear groove acts as a stress riser and the site for crack initiation and propagation. Weibull analysis shows that the wear groove significantly reduces the jet engine fan blade LCF life.
Engine fan blade low cycle fatigue testing
Niedrigfrequenz-Wechsellast-Ermüdungsprüfung eines Gebläseflügels eines Turboluftstrahltriebwerks
AIAA-Papers ; 1-6
1992
6 Seiten, 8 Bilder, 2 Quellen
Aufsatz (Konferenz)
Englisch
Turbomotor , Lüfter , Turbinenwelle , Nebenstromkanal , Schaufelrad , Schaufelbefestigung , Verschleißfestigkeit , Finite-Elemente-Methode , Messmikroskop , Oberflächenbeschaffenheit , Rissbildung , Rissausbreitung , Betriebsverhalten , Prozessoptimierung , Standzeit , Turboluftstrahltriebwerk , Betriebsfestigkeit
Engine fan blade low cycle fatigue testing
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