The Growth of Corner Cracks Under the Conjoint Action of High and Low Cycle Fatigue.
Abstract
Fatigue crack propagation rates have been measured fo Ti-6A1-4V and Ti-5331S aeroengine disc materials using compact tension and corner notched tensile test-pieces. The loadings used simulate both the start-stop operations of aeroengines which lead to low cycle fatigue and the in-flight vibrations which may cause high cycle fatigue. It is suggested that the different fatigue crack growth behavior of Ti-5331S, relative to that of Ti-6A1-4V, arises largely from the greater proportion of crack closure and short crack growth occurring in this alloy. Keywords: Fatigue crack growth, Low/High cycle fatigue, Titanium, aluminum, Vanadium, Minor cycles, Major minor cycling.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1988
- Accession Number
- ADA190510
Entities
People
- B. E. Powell
- I. Henderson
- R. F. Hall