Experimental verification of thickness effect on fatigue crack growth in AA 2124 plate

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F18%3AN0000051" target="_blank" >RIV/00010669:_____/18:N0000051 - isvavai.cz</a>

Výsledek na webu

<a href="http://experimentalni-mechanika.cz/konference/konference/2018.html" target="_blank" >http://experimentalni-mechanika.cz/konference/konference/2018.html</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Experimental verification of thickness effect on fatigue crack growth in AA 2124 plate

Popis výsledku v původním jazyce

Both predictions and experimental results indicate for some materials significant discrepancies between crack propagation data of machined parts from a thick plate to different thinner thicknesses. The different fatigue crack growth behavior under constant and variable amplitude loading can be recognized. The thickness influence could be one of the main possible reasons for this unexpected behavior. The paper deals with a plate thickness of 50 mm made from 2124 T851 aluminum alloy. Crack propagation was investigated for various specimen thicknesses and different loading conditions. No significant thickness influence on the crack propagation behavior occurred both for constant and variable amplitude loading typical for a commuter aircraft loading spectra. It implies that present prediction models are able to predict the crack propagation in this material only using basic material characteristics defined under the constant amplitude loading.

Název v anglickém jazyce

Experimental verification of thickness effect on fatigue crack growth in AA 2124 plate

Popis výsledku anglicky

Both predictions and experimental results indicate for some materials significant discrepancies between crack propagation data of machined parts from a thick plate to different thinner thicknesses. The different fatigue crack growth behavior under constant and variable amplitude loading can be recognized. The thickness influence could be one of the main possible reasons for this unexpected behavior. The paper deals with a plate thickness of 50 mm made from 2124 T851 aluminum alloy. Crack propagation was investigated for various specimen thicknesses and different loading conditions. No significant thickness influence on the crack propagation behavior occurred both for constant and variable amplitude loading typical for a commuter aircraft loading spectra. It implies that present prediction models are able to predict the crack propagation in this material only using basic material characteristics defined under the constant amplitude loading.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20301 - Mechanical engineering

Projekt

<a href="/cs/project/TE02000032" target="_blank" >TE02000032: Výzkumné centrum pokročilých leteckých konstrukcí</a><br>

Návaznosti

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

Rok uplatnění

2018

Kód důvěrnosti údajů

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

Název statě ve sborníku

Experimental Stress Analysis - 56th International Scientific Conference, EAN 2018 - Conference Proceedings

ISBN

978-80-270-4062-9

ISSN

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e-ISSN

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Počet stran výsledku

6

Strana od-do

347-352

Název nakladatele

Czech Society for Mechanics

Místo vydání

Liberec

Místo konání akce

Harrachov

Datum konání akce

5. 6. 2018

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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