Statistic and quantitative fractographic analyses were performed to estimate durability and crack growth period for turbine blades of superalloy EI598 of aircraft engines NK-8-4 and NK-8-2U. Two areas of blades in-service lifetime distribution were discovered. First area of the distribution reflects blade failures because of bad material state had having considerable gradient in grain size. Second area takes place because blades reached their designed durability under in-service simultaneously performed creep and fatigue processes. These processes were analyzed, fatigue crack growth peculiarities for in-service failed blades investigated, and the blade fatigue fracture during 170-190 flights reformed by the fractographic analysis. Causes of the blade fracture in service carefully discussed.
Durability and fatigue cracks growth life of turbine blades of aircraft engine NK-8-2U
Lebensdauer und Ermüdungsrissausbreitungsdauer von Turbinenschaufeln des Flugzeugtriebwerks NK-8-2U
2003
8 Seiten, 4 Bilder, 3 Quellen
Aufsatz (Konferenz)
Englisch
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