Effects of Planar Weld Defects on the Fatigue Properties of 5083/5183 Aluminum Alloy Welds PDF Download
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Author: F. V. Lawrence
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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Book Description
The lack of penetration defects (LOP) can substantially reduce the fatigue life of these welds. The largest defects reduce the fatigue life the most. At 19 ksi., the largest LOP (2a approximately equal to 0.15 in.) can reduce the fatigue life from 80,000 cycles to 2,000 cycles. At 12 ksi., the largest LOP can reduce fatigue life from 4,000,000 cycles to 8,000 cycles. In most cases, the LOP had porosity associated with them. The fatigue crack initiation site usually includes these pores; consequently, the above data reflects the fatigue resistance of LOP with associated porosity.
Author: F. V. Lawrence
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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Book Description
The lack of penetration defects (LOP) can substantially reduce the fatigue life of these welds. The largest defects reduce the fatigue life the most. At 19 ksi., the largest LOP (2a approximately equal to 0.15 in.) can reduce the fatigue life from 80,000 cycles to 2,000 cycles. At 12 ksi., the largest LOP can reduce fatigue life from 4,000,000 cycles to 8,000 cycles. In most cases, the LOP had porosity associated with them. The fatigue crack initiation site usually includes these pores; consequently, the above data reflects the fatigue resistance of LOP with associated porosity.
Author: J. D. Burk
Publisher:
ISBN: 9781581452334
Category : Aluminum alloys
Languages : en
Pages : 14
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Author: F. V Lawrence (Jr)
Publisher:
ISBN: 9781581452051
Category : Aluminum alloys
Languages : en
Pages : 23
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Book Description
The results of the investigation indicate that 5083-5183 welds subjected to fatigue are little affected by porosity if the weld reinforcement is left in place. The weld reinforcement itself is the critical and fatigue limiting notch. Most welds tested with their reinforcement removed gave longer fatigue lives than as-welded tests regardless of porosity level. Porosity most influenced the fatigue lives of the reinforcement removed tests at the lowest stress levels. The radiographic standards currently in use by the U.S. Navy were found to be effective in insuring superior results with reinforcement removed welds. Conversely, few reinforcement removed welds which failed these standards gave shorter fatigue lives than porosity-free, as-welded welds.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978
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Author: Faustin Kalenda Mutombo
Publisher:
ISBN:
Category :
Languages : en
Pages :
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In addition to being one of the highest strength non-heat treatable aluminium alloys, magnesium-alloyed wrought aluminium 5083 displays excellent corrosion resistance and good weldability. Aluminium alloy 6061, alloyed with magnesium and silicon, displays high strength, excellent formability, adequate weldability and good corrosion resistance. These aluminium alloys find application in the ship building and transport industries where 5083 is often joined to 6061 to produce welded structures such as complex I-beams and semi-hollow or hollow channels. This project aimed at characterizing the hardness, tensile properties, corrosion behaviour and fatigue properties (in air and in a 3.5% NaCl solution) of aluminium 5083 and 6061 in the as-received and welded conditions. Plates of 5083-H111 and 6061-T651 aluminium, prepared with double-V or square butt joint preparations, were joined using semi-automatic or fully automatic pulsed gas metal arc welding (GMAW). The pulsed GMAW process allows close control over the welding arc and facilitates the use of lower average heat inputs, thereby improving the bead appearance and mechanical properties. During this investigation, three filler wires were evaluated, namely magnesium-alloyed ER5183 and ER5356 aluminium, and silicon-alloyed ER4043. Hardness measurements revealed a decrease in hardness in the weld metal of the 5083-H111 welds. Dressed welds failed in the weld metal during transverse tensile testing, whereas undressed (as-welded) specimens failed at the weld toe or weld root due to the stress concentration introduced by the weld geometry. Significant softening, attributed to the partial dissolution and coarsening of strengthening precipitates and recrystallization during welding, was observed in the heat-affected zones of the 6061-T651 welds. During tensile testing, failure occurred in the heat-affected zone of all 6061 welds. Welding reduced the room temperature fatigue life of all specimens tested. In the 5083 welds, fatigue cracks initiated preferentially at gas pores, lack-of-fusion type defects and second phase particles in dressed welds, and at the stress concentration presented by the weld toes or the weld root in undressed welds. In 6061 welds, failure occurred preferentially in the softened heat-affected zone of the welds. As a result of improved control over the weld profile and a lower incidence of weld defects, fully automatic welds consistently outperformed semi-automatic welds during fatigue testing. The presence of a corrosive environment (a 3.5% NaCl solution in this investigation) during fatigue testing reduced the fatigue properties of all the samples tested. Corrosion pits formed preferentially at second phase particles or weld defects, and reduced the overall fatigue life by accelerating fatigue crack initiation. Copyright.
Author: Welding Research Council (U.S.)
Publisher:
ISBN:
Category : Welding
Languages : en
Pages : 660
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Author: University of Illinois at Urbana-Champaign. Office of Engineering Publications
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages : 272
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Author:
Publisher:
ISBN:
Category : Naval architecture
Languages : en
Pages : 262
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Author:
Publisher:
ISBN:
Category : Naval architecture
Languages : en
Pages : 1118
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Author: Engineering Foundation, New York. Welding Research Council
Publisher:
ISBN:
Category : Welding
Languages : en
Pages : 628
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