Aluminium Alloy Data Sheet 5083
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Reduction of Out-Of-Plane Distortion in Fillet Welded High Strength Aluminum
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 1974 Reduction of out-of-plane distortion in fillet welded high strength aluminum. Henry, Robert W. Massachusetts Institute of Technology http://hdl.handle.net/10945/17204 REDUCTION OF OUT-OF-PLANE DISTORTION IN FILLET WELDED HIGH STRENGTH ALUMINUM Robert W. Henry il Postgraduate School vionterey, California 93940 REDUCTION OF OUT-OF-PLANE DISTORTION IN FILLET WELDED HIGH STRENGTH ALUMINUM BY Robert W. Henry B.S., U.S. Coast Guard Academy (1969) SUBMITTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREES OF MASTER OF SCIENCE IN OCEAN ENGINEERING AND MASTERS OF SCIENCE IN MECHANICAL ENGINEERING at the Massachusetts Institute of Technology May, 1974 Tii-c DUDLEY KNOX LIBRARY ^STGRADL'ATE SCHOOU - 93940 REDUCTION OF OUT-OF-PLANE DISTORTION IN FILLET WELDED HIGH STRENGTH ALUMINUM by Robert W. Henry Submitted to the Department of Ocean Engineering in May, 1974, in partial fulfillment of the requirements for the degree of Master of Science in Ocean Engineering and Masters of Science in Mechanical Engineering. ABSTRACT Out-of-plane distortion caused by angular changes at fillet welds in aluminum structural panels was examined from two viewpoints. In the first phase of this work a series of experiments was conducted to examine elastic-plastic prestraining of test specimens to be fillet welded as a means of reducing out-of -plane distortion. Data gathered from these tests was correlated with previous experiments in the use of aluminum. A guide in the use of elastic-plastic prestrain- ing for 3/8" and 1/2" was developed. In phase two of this work a two-dimensional program was adapted to the structural aluminum panels used in phase one and tested for accuracy. -
Studies on Properties of Al–Sic Metal Matrix Composite Material for Making IC Engine Valves
Proceedings of the World Congress on Engineering 2018 Vol II WCE 2018, July 4-6, 2018, London, U.K. Studies on Properties of Al–SiC Metal Matrix Composite Material for Making IC Engine Valves Nilamkumar S. Patel, Ashwin D. Patel, Ritesh Kumar Ranjan, Vikas Rai Abstract-Automobile industries are using material substitution the matrix also helps to transfer load among the composite for to build lighter weight, and fuel efficient engines, offering is compound material which differs from alloy due to fact better properties materials of engine components, including that all the individual component retain its characteristic. engine poppet valves and valve seats. Valves and valve seats are very important components that are used at high operating II. EXPERIMENTAL SET-UP temperature to control the flow and volumetric efficient at desired level of engine performance. The present work Stir casting process is liquid state processing. It is simple describes that Al-SiC composite as possible alternate materials and flexible process. In this process, there is mixing of with its unique capacity to give required properties for engine matrix and reinforcement. poppet valves and valve seats. Al-SiC MMC is prepared by In this process, reinforcement particles are added into the powder metallurgy and various casting techniques. In the research a composite is developed by stir casting process by molten matrix metal. And then the proper mixture is done using aluminium alloy with silicon carbide Nano particles and by hand stirring as well as Mechanical stirring. And then substitute sintering operation at 600oC temperature for one this mixture is allowed to pour into the mould shape. -
A Review on Comparison of Aluminium Alloy LM-25 with Al/Sic
International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056 Volume: 05 Issue: 01 | Jan-2018 www.irjet.net p-ISSN: 2395-0072 A review on comparison of Aluminium alloy LM-25 with Al/Sic Rahul Ushir1 , Kunal Gandhi2, Gaurav Dahe3, Vijay Bidgar4, Prof. Vishal Thakre5. 1,2,3,4 BE student Mechanical, SND COE & RC, YEOLA, Maharashtra, India 5Prof. Mechanical, SND COE & RC, YEOLA, Maharashtra, India ---------------------------------------------------------------------***--------------------------------------------------------------------- Abstract- Many industries suffered a great loss of materials and procedures to decrease the wear of devices manufacturing process due to collapse of manufacturing and designing segments. These incorporate change of mass machines due to wear and fail of lubrication. Friction is main properties of the materials, surface medications and cause of wear and energy dissipation. Improving friction can utilization of covering, and so on. In the course of the most make substantial saving. It is obvious that enormous amount recent couple of years, numerous endeavors have been made of the worlds resources are used to overcome friction in the to comprehend the wear conduct of the surfaces in sliding form or another. Lubrication is an effective means of contact and the instrument, which prompts wear. The controlling wear and reducing friction. Hence, for the survival applications of aluminium and its alloys for the machine of machine wear and friction must be decreased parts are increasing day to day in the industry. However, and/controlled carefully. little has been reported on the wear behaviour of aluminium and its alloys with the addition of grain refiner and modifier. Key words: Silicon Carbide(Sic) , aluminium LM25,scanning electron microscope ( SEM ) , metal PROBLEM DEFINITION: matrix composite ( MMCs) . -
Maec.19 70 (University of London) London
COMPLEX & INCREMENTAL STRESS CREEP OF A HIGH STRENGTH ALUMINIUM ALLOY AT ELEVATED TEMPERATURES (ALLOY: HIDUMINIUM RR58 SPECIFICATION DTD 731) by SURINDAR BAHADUR MATHUR Thesis presented in the Department of Mechanical Engineering for the Award of the Doctor of Philosphy in Mechanical Engineering of the University of London. Mechanical Engineering Department Imperial College of Science and Technology mAec.19 70 (University of London) London. ABSTRACT A theory for creep rates under complex and incremental stresses is deduced from experimental data concerning complex creep at elevated temperatures for the test material HIDUMINIUM RR 58 - Specification DID 731. The most important results are for tubular specimens tested at 150°C and 250°C under incremental loads. The analysis of results relates to steady state creep only. Modified relationships in stress equivalence and strain equivalence are proposed to account for thermal softening, polygonization, recrystallization and the resulting exaggerated flow in the direction of the applied shear. (The original equations are based on the hypothesis of Von Mises). A further relationship is suggested between the immediate total energy of distortion and the subsequent creep work rate. Results of the static tests and the results of the tests for creep behaviour under complex loading are presented and compared with the results of static torsion and simple incremental torsion creep tests on the basis of the proposed equations. An appendix describes the complex creep testing machine, furnace, extensometers -
The Effect of Cooling Rate on the Microstructure of A356 Aluminium Alloy
SVOA MATERIALS SCIENCE & TECHNOLOGY (ISSN: 2634-5331) Research https://sciencevolks.com/materials-science/ Volume 2 Issue 4 The Effect of Cooling Rate on the Microstructure of A356 Aluminium Alloy Maftah H. Alkathafi1*, Abdalfattah A. Khalil2, Ayad O. Abdalla3 Affiliations: 1Mechanical Engineering Department, Faculty of Engineering, Sirte University, Libya 2Materials Science Department, Faculty of Engineering, Omer Al-Mukhtar University, Libya. 3College of Mechanical Engineering Technology, Benghazi-Libya. *Corresponding author: Maftah H. Alkathafi* Mechanical Engineering Department, Faculty of Engineering, Sirte University, Libya Received: December 10, 2020 Published: December 31, 2020 Abstract: In this study a fast-cooling technology is employed for a cast iron mould to prepare cast A356 aluminium alloy by solidifica- tion of the molten metal. The cooling rate is achieved by pouring the molten alloy into a preheating permanent mould at different temperatures (25, 100, 200, 300 and 4000C) for cast samples with 40 mm inside diameter and 200 mm height. The samples considered are analyzed by optical microscopy, scanning electron microscopy (SEM), and EDS X-ray analysis (EDS). The effects of cooling rate on the morphology of α – aluminum and eutectic silicon of A356 alloy have been studied. The results showed that the dendritic structure of α-phase was broken and converted into a somewhat globular grain structure and the coarse acicular eutectic silicon trend to be broken and converted into short sticks or small rounded in other cases. Keywords: A356 Aluminum alloy, Grain refinement, Cooling rate, SEM, EDS, Microstructure. 1. Introduction Aluminium alloys have attractive physical and mechanical properties. They are lightweight, low costs production, easy to machine and have good recycling possibilities up to 95 % [1]. -
Aluminium Alloy - 6262 - T6 Extrusions
Aluminium Alloy - 6262 - T6 Extrusions SPECIFICATIONS CHEMICAL COMPOSITION Commercial 6262 BS EN 573-3:2009 Alloy 6262 EN 6262 Element % Present Magnesium (Mg) 0.80 - 1.20 Aluminium alloy 6262 is a heat treatable alloy with Copper (Cu) 0.15 - 1.40 very good corrosion resistance and strength. Additions of bismuth to the alloy mean that 6262 has excellent Silicon (Si) 0.40 - 0.80 machinability and surface finish. Lead (Pb) 0.40 - 0.70 High-speed steel or carbide tooling can be used to obtain smooth finishes. Heavy cutting requires oil Bismuth (Bi) 0.40 - 0.70 lubricant but light cutting can be done dry. Iron (Fe) 0.0 - 0.70 Alloy 6262 can be used in place of 2011 when higher corrosion resistance and better anodising response is Zinc (Zn) 0.0 - 0.25 required. Chromium (Cr) 0.04 - 0.14 Applications Titanium (Ti) 0.0 - 0.15 6262 is commonly used in the manufacture of: Manganese (Mn) 0.0 - 0.15 Screw machine products Camera parts Others (Total) 0.0 - 0.15 Nuts Other (Each) 0.0 - 0.05 Couplings Aluminium (Al) Balance Marine fittings Decorative hardware and appliance fittings Hinge pins Oil line fittings ALLOY DESIGNATIONS Valves and valve parts Aluminium alloy 6262 also corresponds to the following standard designations and specifications but may not PLEASE NOTE: Due to European Environmental be a direct equivalent: Protection Directives: AA6262 # 2000/53/CE-ELV – For the automotive sector Al 1.0Mg 0.6Si Pb # 2002/95/CE-RoHS – For the electrical and A96262 electronics sector This alloy has been replaced by Alloy 6026 which has a PLEASE NOTE: Due to European Environmental lower Lead content. -
Fatigue Behavior of 2618-T851 Aluminum Alloy Under Uniaxial and Multiaxial Loadings
Open Archive Toulouse Archive Ouverte (OATAO) OATAO is an open access repository that collects the wor of some Toulouse researchers and ma es it freely available over the web where possible. This is an author's version published in: https://oatao.univ-toulouse.fr/24572 Official URL : https://doi.org/10.1016/j.ijfatigue.2019.105322 To cite this version : BenaÕssa, Malek and Mabru, Catherine and Chaussumier, Michel Fatigue behavior of 2618-T851 aluminum alloy under uniaxial and multiaxial loadings. (2020) International Journal of Fatigue, 131 (105322). 1-9. ISSN 0142-1123 Any correspondence concerning this service should be sent to the repository administrator: [email protected] Fatigue behavior of 2618-T851 aluminum alloy under uniaxial and multiaxial loadings ⁎ Benaïssa Malek, Catherine Mabru, Michel Chaussumier Université de Toulouse, Institut Clément Ader (ICA), UMR CNRS 5312, UPS/INSA/ISAE/ Mines Albi, 3 Rue Caroline Aigle, 31400 Toulouse, France ABSTRACT Keywords: AA2618 aeronautical aluminum alloy has been largely used in the past, especially in well-known Concorde AA2618-T851 aircraft, developed during sixties decade. In more recent aircraft, this alloy has been largely replaced by others Multiaxial fatigue such as 7075 which present greater fatigue resistance. Forgotten for a time, AA2618 comes back in new aircrafts Roughness for structural parts submitted to fatigue loading at high temperature because of only a slight decrease of fatigue Crossland criterion resistance of this alloy compared to room temperature fatigue resistance. In this paper, a complete fatigue characterization of 2618-T851 aluminum alloy is presented: fatigue tests under uniaxial tensile or torsion cyclic loadings, with mean tensile or shear stress have been realized; fatigue tests under combined tensile-torsion, in or out-of-phase have also been conducted as well as some combined tensile-torsion-internal pressure fatigue tests. -
Tribological Behavior and Hardness Properties of Heat Treated Al 7075-Beryl-Graphene Hybrid Metal Matrix Composites
International Journal of Recent Technology and Engineering (IJRTE) ISSN: 2277-3878, Volume-8 Issue-3, September 2019 Tribological Behavior and Hardness Properties of Heat Treated Al 7075-Beryl-Graphene Hybrid Metal Matrix Composites Shanawaz Patil, Mohamed Haneef mirror frames, house members, serving trays and cooking Abstract— The emerging technologies and trends of the utensils. Even in the field of engineering applications, the present generation require downsizing the unwieldy structures to aluminum and its alloys plays vigorous role as an aerospace, lightweight structures. Aluminum matrix composites are tailored space, and automotive components material of increasing candidate materials for aerospace applications due to their outstanding greater strength to weight ratio and low wear rate. In value because of its properties which includes diverse range this study, Al7075 alloy-Beryl-Graphene hybrid composites are of uses are appearance, lightweight and has a low density of developed by using stir casting process. Graphene weight range 2.7 to 2.8 gm/cm3 which is almost one-third of steel percentage was varied from 0 wt. % to 2 wt. % in steps of 0.5 wt. %. (7.83 gmcm3)[-,5]. One of the foremost usually used metal Whereas for Beryl 6 wt. % is used thorough out the study. The alloy for structural application is Al7075 due to its enticing casted specimens were heat-treated at T6 solutionizing wide-ranging properties like low density, improved strength, temperature of 530±5oC for 8 hours. After the heat treatment the specimen are quenched in boiling Water and Ice. The ductility, toughness, and resistance to fatigue. Al7075 alloy microstructure of the newly developed hybrid MMCs has been has been extensively used in aircraft structure elements and investigated by TEM and SEM. -
Machining of Aluminum and Aluminum Alloys / 763
ASM Handbook, Volume 16: Machining Copyright © 1989 ASM International® ASM Handbook Committee, p 761-804 All rights reserved. DOI: 10.1361/asmhba0002184 www.asminternational.org MachJning of Aluminum and AlumJnum Alloys ALUMINUM ALLOYS can be ma- -r.. _ . lul Tools with small rake angles can normally chined rapidly and economically. Because be used with little danger of burring the part ," ,' ,,'7.,','_ ' , '~: £,~ " ~ ! f / "' " of their complex metallurgical structure, or of developing buildup on the cutting their machining characteristics are superior ,, A edges of tools. Alloys having silicon as the to those of pure aluminum. major alloying element require tools with The microconstituents present in alumi- larger rake angles, and they are more eco- num alloys have important effects on ma- nomically machined at lower speeds and chining characteristics. Nonabrasive con- feeds. stituents have a beneficial effect, and ,o IIR Wrought Alloys. Most wrought alumi- insoluble abrasive constituents exert a det- num alloys have excellent machining char- rimental effect on tool life and surface qual- acteristics; several are well suited to multi- ity. Constituents that are insoluble but soft B pie-operation machining. A thorough and nonabrasive are beneficial because they e,,{' , understanding of tool designs and machin- assist in chip breakage; such constituents s,~ ,.t ing practices is essential for full utilization are purposely added in formulating high- of the free-machining qualities of aluminum strength free-cutting alloys for processing in alloys. high-speed automatic bar and chucking ma- Strain-hardenable alloys (including chines. " ~ ~p /"~ commercially pure aluminum) contain no In general, the softer ailoys~and, to a alloying elements that would render them lesser extent, some of the harder al- c • o c hardenable by solution heat treatment and ,p loys--are likely to form a built-up edge on precipitation, but they can be strengthened the cutting lip of the tool. -
Aluminium Alloys Chemical Composition Pdf
Aluminium alloys chemical composition pdf Continue Alloy in which aluminum is the predominant lye frame of aluminum welded aluminium alloy, manufactured in 1990. Aluminum alloys (or aluminium alloys; see spelling differences) are alloys in which aluminium (Al) is the predominant metal. Typical alloy elements are copper, magnesium, manganese, silicon, tin and zinc. There are two main classifications, namely casting alloys and forged alloys, both further subdivided into heat-treatable and heat-free categories. Approximately 85% of aluminium is used for forged products, e.g. laminated plates, foils and extrusions. Aluminum cast alloys produce cost-effective products due to their low melting point, although they generally have lower tensile strength than forged alloys. The most important cast aluminium alloy system is Al–Si, where high silicon levels (4.0–13%) contributes to giving good casting features. Aluminum alloys are widely used in engineering structures and components where a low weight or corrosion resistance is required. [1] Alloys composed mostly of aluminium have been very important in aerospace production since the introduction of metal leather aircraft. Aluminum-magnesium alloys are both lighter than other aluminium alloys and much less flammable than other alloys containing a very high percentage of magnesium. [2] Aluminum alloy surfaces will develop a white layer, protective of aluminum oxide, if not protected by proper anodization and/or dyeing procedures. In a wet environment, galvanic corrosion can occur when an aluminum alloy is placed in electrical contact with other metals with a more positive corrosion potential than aluminum, and an electrolyte is present that allows the exchange of ions. -
Aluminum Alloy Weldability: Identification of Weld Solidification Cracking Mechanisms Through Novel Experimental Technique and Model Development
Dipl.-Ing. Nicolas Coniglio Aluminum Alloy Weldability: Identifi cation of Weld Solidifi cation Cracking Mechanisms through Novel Experimental Technique and Model Development BAM-Dissertationsreihe • Band 40 Berlin 2008 Die vorliegende Arbeit entstand an der BAM Bundesanstalt für Materialforschung und -prüfung. Impressum Aluminum Alloy Weldability: Identifi cation of Weld Solidifi cation Cracking Mechanisms through Novel Experimental Technique and Model Development 2008 Herausgeber: BAM Bundesanstalt für Materialforschung und -prüfung Unter den Eichen 87 12205 Berlin Telefon: +49 30 8104-0 Telefax: +49 30 8112029 E-Mail: [email protected] Internet: www.bam.de Copyright © 2008 by BAM Bundesanstalt für Materialforschung und -prüfung Layout: BAM-Arbeitsgruppe Z.64 ISSN 1613-4249 ISBN 978-3-9812354-3-2 Aluminum Alloy Weldability: Identification of Weld Solidification Cracking Mechanisms through Novel Experimental Technique and Model Development Dissertation zur Erlangung des akademischen Grades Doktor-Ingenieur (Dr.-Ing.) genehmigt durch die Fakultät für Maschinenbau der Otto-von-Guericke-Universität Madgeburg am 02.06.08 vorgelegte Dissertation von Dipl.-Ing. Nicolas Coniglio Thesis Committee: Prof. Dr.-Ing. A. Bertram Prof. Dr.-Ing. T. Böllinghaus Prof. C.E. Cross Prof. S. Marya Date of Examination: 23 October 2008 Abstract Abstract The objective of the present thesis is to make advancements in understanding solidification crack formation in aluminum welds, by investigating in particular the aluminum 6060/4043 system. Alloy 6060 is typical of a family of Al-Mg-Si extrusion alloys, which are considered weldable only when using an appropriate filler alloy such as 4043 (Al-5Si). The effect of 4043 filler dilution (i.e. weld metal silicon content) on cracking sensitivity and solidification path of Alloy 6060 welds are investigated. -
International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys
International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys 1525 Wilson Boulevard, Arlington, VA 22209 www.aluminum.org With Support for On-line Access From: Aluminum Extruders Council Australian Aluminium Council Ltd. European Aluminium Association Japan Aluminium Association Alro S.A, R omania Revised: January 2015 Supersedes: February 2009 © Copyright 2015, The Aluminum Association, Inc. Unauthorized reproduction and sale by photocopy or any other method is illegal . Use of the Information The Aluminum Association has used its best efforts in compiling the information contained in this publication. Although the Association believes that its compilation procedures are reliable, it does not warrant, either expressly or impliedly, the accuracy or completeness of this information. The Aluminum Association assumes no responsibility or liability for the use of the information herein. All Aluminum Association published standards, data, specifications and other material are reviewed at least every five years and revised, reaffirmed or withdrawn. Users are advised to contact The Aluminum Association to ascertain whether the information in this publication has been superseded in the interim between publication and proposed use. CONTENTS Page FOREWORD ........................................................................................................... i SIGNATORIES TO THE DECLARATION OF ACCORD ..................................... ii-iii REGISTERED DESIGNATIONS AND CHEMICAL COMPOSITION