Parida, BK and Nicholas, T (1994) Elevated temperature fatigue crack growth behavior of Ti-1100. Fatigue and Fracture of Engineering Materials and Structures, 17 (5). pp. 551-561.Full text not available from this repository.
The fatigue crack growth behavior of Ti-1100 is analyzed at elevated temperatures to evaluate the effects of mechanical and environmental variables. Experiments conducted over a wide range of frequencies from 0.01 Hz to 200 Hz indicate a strong dependence of the growth rate upon cyclic loading frequency. Superposition of hold time at maximum and minimum loads over a baseline 1.0 Hz cyclic loading frequency produces an insignificant variation in crack growth rate, which may be attributed to the combined effects of enhanced environmental degradation, crack-tip blunting and increased asperity-induced closure level in this material. It is deduced that a hold time at maximum load results in an interaction of the environmental effects with a retardation effect due to a crack tip blunting as a consequence of creep under maximum applied load, whereas for hold at minimum loads, extensive crack-branching and micro-cracking appear to enhance crack closure loads resulting in lower crack growth rates. A linear superposition model is employed to account for the complex interactions due to fatigue, creep and environmental degradation.
|Item Type:||Journal Article|
|Uncontrolled Keywords:||Crack propagation; Cracks; Creep; Degradation; Fatigue of materials; Fatigue testing; High temperature effects; Loads (forces); Mathematical models; Asperity induced closure level; Crack tip blunting; Cyclic loading frequency; Environmental degradation; Extensive crack branching; Linear superposition model; Titanium alloy 1100; Titanium alloys;|
|Subjects:||AERONAUTICS > Aircraft Design, Testing & Performance|
|Division/Department:||Structural Integrity Division, Other|
|Depositing User:||Mr Vijaianand SK|
|Date Deposited:||10 Mar 2005|
|Last Modified:||24 May 2010 09:38|
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