Overload Effect on High Cycle Fatigue and Crack Propagation of Some Metastable Beta Titanium-vanadium Alloys PDF Download

Author: Eui Whee Lee
Publisher:
ISBN:
Category : Titanium alloys
Languages : en
Pages : 170

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Author: Eui Whee Lee
Publisher:
ISBN:
Category :
Languages : en
Pages : 39

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The crack retardation response due to single- and multiple-cycle overload of two titanium vanadium alloys (24 and 32 wt. pct. V) has been studied. It has been observed that the degree of retardation depends upon the vanadium content of the alloy, the load ratio, the number of overload cycles and the magnitude of the peak load. Fractographic observations show that the cracking mode may be changed in the overload affected zone from that in the preoverload region. These results seem to incidcate that the retardation behavior is mainly due to the compressive residual stresses arising as a consequence of the overload. The degree of retardation depends not only on the loading variables, but also on the material parameters like the monotonic and cyclic deformation behavior, and the stress-strain response. (Author).

Author: Saghana B. Chakrabortty
Publisher:
ISBN:
Category :
Languages : en
Pages : 37

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The fatigue crack propagation behavior of three titanium-vanadium alloys (24, 28 and 32 wt.% V) which have (tensile) deformation modes ranging from coarse twinning to wavy and planar slip has been measured in laboratory air and correlated with their low cycle fatigue properties and microstructure. The fatigue crack growth rate of alloys with similar microstructures but different deformation modes, and of alloys with similar deformation modes but different microstructures have been compared. Increasing the deformation barrier mean free path and improving low cycle fatigue properties has been observed to reduce the fatigue crack growth rate at low and intermediate Delta K levels. The fatigue crack growth data have been compared with that calculated from equations which use microstructure and low cycle fatigue parameters. The predictive capability of these equations which contain only measurable parameters has been found to be quite adequate. (Author).

Author:
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Category : Aeronautics
Languages : en
Pages : 1370

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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Author: R. Shover
Publisher:
ISBN:
Category : Fatigue crack growth
Languages : en
Pages : 12

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The effects of overloads on the fatigue crack growth behavior of the high trength ?/? titanium alloy Ti-6-22-22 have been investigated. Fatigue cracks were grown at a baseline R level of 0.1, and single overloads, ranging in magnitude from 2-3 times the baseline level, were applied to determine the effect of the overloads on subsequent fatigue crack growth behavior. Because of the high yield strength of the alloy, 1225 MPa, the number of delay cycles following an overload was not as pronounced as in alloys of lesser strength. A principal effect of an overload in this titanium alloy was to increase the threshold for fatigue crack growth. An experimental procedure based upon the increase in threshold level was adopted to determine the maximum level of crack closure resulting from an overload.

Author: Eui Whee Lee
Publisher:
ISBN:
Category : Thanium alloys
Languages : en
Pages : 220

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Author: Eric F. J. Von Euw
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 86

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Author: Eric F. J. Von Euw
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 172

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Author:
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ISBN:
Category : Metallurgy
Languages : en
Pages : 1040

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Author: A. Raith
Publisher:
ISBN:
Category : Titanium alloys
Languages : en
Pages : 68

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The fatigue crack growth rate tests of water quenched Corona-5 (Ti-4.5Al-1.5Cr-5Mo) and Ti-6Al-4V alloy were conducted in air at room temperature. The effect of the presence of the metastable retained beta phase on the fatigue crack growth rate was examined in this research. The specimens were heat treated and water quenched to have unstable beta phase that could be transformed to martensite during the fatigue crack growth testing. As quenched specimens were compared with specimens in the mill annealed condition. The fatigue crack growth rates of all the specimens were in the same order of magnitude regardless of the heat treatment. From this research it was shown that in Corona-5 and Ti-6Al-4V alloys the fatigue crack growth rates were not affected by the strain induced martensitic transformation.