Evaluation of fatigue crack growth rates and threshold conditions in an Al 2124-T851 alloy at different load asymmetry considering microstructure orientation.

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F25797000%3A_____%2F14%3A%230000481" target="_blank" >RIV/25797000:_____/14:#0000481 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.scientific.net/KEM" target="_blank" >http://www.scientific.net/KEM</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.4028/www.scientific.net/KEM.577-578.321" target="_blank" >10.4028/www.scientific.net/KEM.577-578.321</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Evaluation of fatigue crack growth rates and threshold conditions in an Al 2124-T851 alloy at different load asymmetry considering microstructure orientation.

Popis výsledku v původním jazyce

Results of a fairly comprehensive experimental programme aimed at evaluation of fatigue crack growth (FCG) rates in an aircraft Al 2124 alloy in T851 state, after hot rolling, solution annealing, small plastic strain and artificial ageing are presented and discussed. Measurement was performed not only in the region of stable crack growth, but also in the threshold region enabling to estimate threshold values of stress intensity factor range using method of regression analyses. FCG rates were evaluated in both L-T and T-S directions to evaluate sensitivity of FCG resistance on different microstructure orientation. Different load asymmetry conditions R = Fmin / F max were used, namely R = 0.1 and 0.6. Repeated measurements in more than one specimen at each condition enabled to evaluate reproducibility, scatter of measurement and to perform eventually probabilistic assessment. The reproducibility of measurement was particularly good for L-T orientation. In this case, threshold values were

Název v anglickém jazyce

Evaluation of fatigue crack growth rates and threshold conditions in an Al 2124-T851 alloy at different load asymmetry considering microstructure orientation.

Popis výsledku anglicky

Results of a fairly comprehensive experimental programme aimed at evaluation of fatigue crack growth (FCG) rates in an aircraft Al 2124 alloy in T851 state, after hot rolling, solution annealing, small plastic strain and artificial ageing are presented and discussed. Measurement was performed not only in the region of stable crack growth, but also in the threshold region enabling to estimate threshold values of stress intensity factor range using method of regression analyses. FCG rates were evaluated in both L-T and T-S directions to evaluate sensitivity of FCG resistance on different microstructure orientation. Different load asymmetry conditions R = Fmin / F max were used, namely R = 0.1 and 0.6. Repeated measurements in more than one specimen at each condition enabled to evaluate reproducibility, scatter of measurement and to perform eventually probabilistic assessment. The reproducibility of measurement was particularly good for L-T orientation. In this case, threshold values were

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JL - Únava materiálu a lomová mechanika

OECD FORD obor

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Projekt

<a href="/cs/project/FR-TI2%2F557" target="_blank" >FR-TI2/557: Projekt MOSTA - Modernizace malého dopravního letounu za účelem zvýšení efektivnosti a ekonomie jeho provozu</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2014

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

Key Engineering Materials

ISSN

1013-9826

e-ISSN

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Svazek periodika

577-578

Číslo periodika v rámci svazku

2014

Stát vydavatele periodika

CH - Švýcarská konfederace

Počet stran výsledku

4

Strana od-do

321-324

Kód UT WoS článku

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EID výsledku v databázi Scopus

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