Load and Environment Interactions in Fatigue Crack Growth Under Spectrum Loading PDF Download
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Author: R. P. Wei
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
The importance of delay (or, retardation in the rate of fatigue crack growth) produced by load interactions in variable-amplitude loading on the accurate prediction of fatigue lives of aircraft and other engineering structures has been recognized for some time and has begun to receive greater attention in recent years. Recent investigations showed that the effects of delay can be quite large, and that these effects need to be taken into account in developing improved fatigue analysis procedures for aircraft and other engineering structures. A number of models (based on the concepts of crack closure, residual stress intensity factor, etc.) have been proposed to account for the effects of delay. These models, while successfully predicting trends in the rate of fatigue crack growth for randomized load spectra, appear to break down for ordered spectra. Several basic problems contributed to the lack of complete success, and needs to be resolved in the development of improved models for predicting load interaction effects (chiefly delay) on fatigue crack growth.
Author: R. P. Wei
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
The importance of delay (or, retardation in the rate of fatigue crack growth) produced by load interactions in variable-amplitude loading on the accurate prediction of fatigue lives of aircraft and other engineering structures has been recognized for some time and has begun to receive greater attention in recent years. Recent investigations showed that the effects of delay can be quite large, and that these effects need to be taken into account in developing improved fatigue analysis procedures for aircraft and other engineering structures. A number of models (based on the concepts of crack closure, residual stress intensity factor, etc.) have been proposed to account for the effects of delay. These models, while successfully predicting trends in the rate of fatigue crack growth for randomized load spectra, appear to break down for ordered spectra. Several basic problems contributed to the lack of complete success, and needs to be resolved in the development of improved models for predicting load interaction effects (chiefly delay) on fatigue crack growth.
Author: T. T. Shih
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
The influences of environment on delay and on fatigue crack growth under programmed loading were examined for a mill annealed Ti-6Al-4V alloy. Test environments included dehumidified argon, air (with 30-60% relative humidity), distilled water, and 3.5% NaCl solution. The effects of load sequence and block size on fatigue under programmed loads were investigated also. Experimental results show that the mildly aggressive environments (atmospheric moisture and distilled water) have little effect on delay. Salt solution, on the other hand, has a significant effect on delay and on crack growth under programmed loading; the effect on delay being dependent on frequency or hold-time. Both load sequence and block size can significantly alter fatigue life under programmed loading. The need for further fundamental understanding of load and environment interactions in fatigue is discussed. (Modified author abstract).
Author: MS. Rosenfeld
Publisher:
ISBN:
Category : Crack growth
Languages : en
Pages : 19
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Book Description
Recent research into the crack growth behavior of aircraft landing gear steels shows that combinations of aggressive chemical environment and high sustained loading can cause significant reduction in the fatigue crack growth life of 300M steel. Crack growth behaviors of 300M and HP 9-4-0.30 steels are compared for continuous salt water immersion and alternate immersion in synthetic sea water environments. An analysis approach which sums the crack growth due to cyclic loading in an inert environment is shown to accurately correlate and predict the combined effects of chemical environment and mechanical loading on crack growth. Crack growth behavior under landing gear stress spectra typical of Air Force and Navy usage is compared.
Author: Stoyan Ivanov Stoychev
Publisher:
ISBN:
Category : Fracture mechanics
Languages : en
Pages : 0
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Author:
Publisher: ASTM International
ISBN:
Category : Alloys
Languages : en
Pages : 362
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Author: R. M. Pelloux
Publisher: American Society of Civil Engineers
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 216
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Author: DC. Maxwell
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 14
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Book Description
Effects of temperature, frequency, and cycles with superimposed hold times are evaluated in Ti-1100 in order to study the complex creep-fatigue-environment interactions in this material. Crack growth rate tests conducted at a cyclic loading frequency of 1.0 Hz show that raising the temperature from 593 to 650°C has only a slightly detrimental effect on crack growth rate, although these temperatures produce growth rates significantly higher than at room temperature. From constant ?K tests, the effects of temperature at constant frequency show a minimum crack growth rate at 250°C. From the minimum crack growth rate at 250°C, the crack growth rate increases linearly with temperature. Increases in frequency at constant temperatures of 593 and 650°C produce a continuous decrease in growth rate in going from 0.001 to 1.0 Hz, although the behavior is primarily cycle dependent in this region. Tests at 1.0 Hz with superimposed hold times from 1 to 1000 s are used to evaluate creep-fatigue-environment interactions. Hold times at maximum load are found to initially decrease and then increase the cyclic crack growth rate with increasing duration. This is attributed to crack-tip blunting during short hold times and environmental degradation at long hold times. Hold times at minimum load show no change in growth rates, indicating that there is no net environmental degradation to the bulk material beyond that experienced during the baseline 1 Hz cycling.
Author: Ralph Ivan Stephens
Publisher: ASTM International
ISBN:
Category : Alloys
Languages : en
Pages : 345
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Author: American Society for Testing and Materials
Publisher: ASTM International
ISBN: 9780803100503
Category : Corrosion and anti-corrosives
Languages : en
Pages : 344
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