Short fatigue crack growth in an aircraft Al-alloy of a 7075 type after shot peening

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F25797000%3A_____%2F14%3A%230000473" target="_blank" >RIV/25797000:_____/14:#0000473 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.journals.elsevier.com/surface-and-coatings-technology/" target="_blank" >http://www.journals.elsevier.com/surface-and-coatings-technology/</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.surfcoat.2012.06.008" target="_blank" >10.1016/j.surfcoat.2012.06.008</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Short fatigue crack growth in an aircraft Al-alloy of a 7075 type after shot peening

Popis výsledku v původním jazyce

An effect of shot peening with two groups of parameters representing limits for practical use in service on growth of physically short fatigue cracks in a 2.4. mm thick sheet of an aircraft V-95 Al-alloy (a type of a 7075 alloy), clad with a 7072 Al-alloy (Al-Zn1) was investigated. Using the improved experimental methodology, physically short fatigue cracks of the length from 0.2. mm to more than 3. mm, most of them between 0.8 and 1.5. mm, were prepared under high cycle fatigue repeated tensile loadingof the constant nominal stress range 160. MPa, load asymmetry R. =. 0. Specimens with existing short fatigue cracks together with some specimens with no cracks were then shot peened using two different groups of parameters. Microhardness measurement andinformative measurement of residual stresses near the peened edges were carried out. Development of crack growth after shot peening were measured and compared with crack growth in specimens without shot peening. Retardation of crack grow

Název v anglickém jazyce

Short fatigue crack growth in an aircraft Al-alloy of a 7075 type after shot peening

Popis výsledku anglicky

An effect of shot peening with two groups of parameters representing limits for practical use in service on growth of physically short fatigue cracks in a 2.4. mm thick sheet of an aircraft V-95 Al-alloy (a type of a 7075 alloy), clad with a 7072 Al-alloy (Al-Zn1) was investigated. Using the improved experimental methodology, physically short fatigue cracks of the length from 0.2. mm to more than 3. mm, most of them between 0.8 and 1.5. mm, were prepared under high cycle fatigue repeated tensile loadingof the constant nominal stress range 160. MPa, load asymmetry R. =. 0. Specimens with existing short fatigue cracks together with some specimens with no cracks were then shot peened using two different groups of parameters. Microhardness measurement andinformative measurement of residual stresses near the peened edges were carried out. Development of crack growth after shot peening were measured and compared with crack growth in specimens without shot peening. Retardation of crack grow

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

—

Návaznosti

Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2014

Kód důvěrnosti údajů

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

Název periodika

Surface and Coatings Technology

ISSN

0257-8972

e-ISSN

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Svazek periodika

243

Číslo periodika v rámci svazku

březen 2014

Stát vydavatele periodika

NL - Nizozemsko

Počet stran výsledku

8

Strana od-do

20-27

Kód UT WoS článku

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EID výsledku v databázi Scopus

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