Standard Tables for Chromel-Alumel Thermocouples
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Development of Filler Metals and Procedures for Vacuum Brazing Of
Development of Filler Metals and Procedures for Vacuum Brazing of Aluminum Several brazing filler metal compositions have been developed which offer significant improvements over existing compositions. They braze in vacuum at temperatures lower than normal flow temperatures and have equal or better flowability BY W. J. WERNER, G. M. SLAUGHTER AND F. B. GURTNER Introduction ry cleanliness levels under production vantages. As a single entity, it was This report documents work per conditions. The maximum allowable immediately more desirable from a formed toward the development of lag between cleaning and brazing was cleaning, assembling and material found to be 12 hours. handling standpoint. Metallurgically, new brazing filler metals for vacuum- 2 fluxless brazing (1 X 10~6 torr) C. S. Beuyukian developed tech the 4045 brazing filler metal with its certain aluminum alloys of interest to niques for vacuum or inert gas fluxless lower silicon content allowed greater the Army. The base metals under brazing of aluminum cold plates for latitude in processing parameters than consideration were alloys 6061, 2219, use in Apollo command modules. In did alloy No. 718. 7075 and 2024. Brazing filler metal this work, brazing filler metal No. 718 Finally, the workers at Aeronca, and No. 23 brazing sheet were evalu Inc. completed a study on inert gas flow temperatures needed for these 3 alloys encompass the temperature ated. Alloy No. 718 is nominally 88% brazing of aluminum in early 1967. range 900 to 1200F. Specifically, the aluminum, 12% silicon; No. 23 braz Their work was concerned with de contract called for the development of ing sheet is comprised of 6951 base velopment of high strength brazed alloys with flow temperatures of 950, alloy clad on one side with 4045 aluminum honeycomb structures 1000, and 1050F. -
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 -
Apollo Space Suit
APOLLO SPACE S UIT 1962–1974 Frederica, Delaware A HISTORIC MECHANICAL ENGINEERING LANDMARK SEPTEMBER 20, 2013 DelMarVa Subsection Histor y of the Apollo Space Suit This model would be used on Apollo 7 through Apollo 14 including the first lunar mission of Neil Armstrong and Buzz International Latex Corporation (ILC) was founded in Aldrin on Apollo 11. Further design improvements were made to Dover, Delaware in 1937 by Abram Nathanial Spanel. Mr. Spanel improve mobility for astronauts on Apollo 15 through 17 who was an inventor who became proficient at dipping latex material needed to sit in the lunar rovers and perform more advanced to form bathing caps and other commercial products. He became mobility exercises on the lunar surface. This suit was known as famous for ladies apparel made under the brand name of Playtex the model A7LB. A slightly modified ILC Apollo suit would also go that today is known worldwide. Throughout WWII, Spanel drove on to support the Skylab program and finally the American-Soyuz the development and manufacture of military rubberized products Test Program (ASTP) which concluded in 1975. During the entire to help our troops. In 1947, Spanel used the small group known time the Apollo suit was produced, manufacturing was performed as the Metals Division to develop military products including at both the ILC plant on Pear Street in Dover, Delaware, as well as several popular pressure helmets for the U.S. Air Force. the ILC facility in Frederica, Delaware. In 1975, the Dover facility Based upon the success of the pressure helmets, the Metals was closed and all operations were moved to the Frederica plant. -
Microstructual and Thermal Analysis of Aluminum-Silicon and Magnesium-Aluminum Alloys Subjected to High Cooling Rates
University of Windsor Scholarship at UWindsor Electronic Theses and Dissertations Theses, Dissertations, and Major Papers 2012 Microstructual and Thermal Analysis of Aluminum-Silicon and Magnesium-Aluminum Alloys Subjected to High Cooling Rates Paul Marchwica University of Windsor Follow this and additional works at: https://scholar.uwindsor.ca/etd Recommended Citation Marchwica, Paul, "Microstructual and Thermal Analysis of Aluminum-Silicon and Magnesium-Aluminum Alloys Subjected to High Cooling Rates" (2012). Electronic Theses and Dissertations. 5572. https://scholar.uwindsor.ca/etd/5572 This online database contains the full-text of PhD dissertations and Masters’ theses of University of Windsor students from 1954 forward. These documents are made available for personal study and research purposes only, in accordance with the Canadian Copyright Act and the Creative Commons license—CC BY-NC-ND (Attribution, Non-Commercial, No Derivative Works). Under this license, works must always be attributed to the copyright holder (original author), cannot be used for any commercial purposes, and may not be altered. Any other use would require the permission of the copyright holder. Students may inquire about withdrawing their dissertation and/or thesis from this database. For additional inquiries, please contact the repository administrator via email ([email protected]) or by telephone at 519-253-3000ext. 3208. Microstructual and Thermal Analysis of AlSi and MgAl Alloys Subjected to High Cooling Rates By Paul C. Marchwica A Thesis Submitted to the Faculty of Graduate Studies through the Department of Mechanical, Automotive and Materials Engineering in Partial Fulfillment of the Requirements for the Degree of Master of Applied Science at the University of Windsor Windsor, Ontario, Canada 2012 © 2012 P. -
Pub Date Abstract
DOCUMENT RESUME ED 058 456 VT 014 597 TITLE Exploring in Aeronautics. An Introductionto Aeronautical Sciences. INSTITUTION National Aeronautics and SpaceAdministration, Cleveland, Ohio. Lewis Research Center. REPORT NO NASA-EP-89 PUB DATE 71 NOTE 398p. AVAILABLE FROMSuperintendent of Documents, U.S. GovernmettPrinting Office, Washington, D.C. 20402 (Stock No.3300-0395; NAS1.19;89, $3.50) EDRS PRICE MF-$0.65 HC-$13.16 DESCRIPTORS Aerospace Industry; *AerospaceTechnology; *Curriculum Guides; Illustrations;*Industrial Education; Instructional Materials;*Occupational Guidance; *Textbooks IDENTIFIERS *Aeronatics ABSTRACT This curriculum guide is based on a year oflectures and projects of a contemporary special-interestExplorer program intended to provide career guidance and motivationfor promising students interested in aerospace engineering and scientific professions. The adult-oriented program avoidstechnicality and rigorous mathematics and stresses real life involvementthrough project activity and teamwork. Teachers in high schoolsand colleges will find this a useful curriculum resource, w!th manytopics in various disciplines which can supplement regular courses.Curriculum committees, textbook writers and hobbyists will also findit relevant. The materials may be used at college level forintroductory courses, or modified for use withvocationally oriented high school student groups. Seventeen chapters are supplementedwith photographs, charts, and line drawings. A related document isavailable as VT 014 596. (CD) SCOPE OF INTEREST NOTICE The ERIC Facility has assigned this document for processing to tri In our judgement, thisdocument is also of interest to the clearing- houses noted to the right. Index- ing should reflect their special points of view. 4.* EXPLORING IN AERONAUTICS an introduction to Aeronautical Sciencesdeveloped at the NASA Lewis Research Center, Cleveland, Ohio. -
Temperature Measurement
mywbut.com 14 Temperature measurement 14.1 Principles of temperature measurement Temperature measurement is very important in all spheres of life and especially so in the process industries. However, it poses particular problems, since temperature measurement cannot be related to a fundamental standard of temperature in the same way that the measurement of other quantities can be related to the primary standards of mass, length and time. If two bodies of lengths l1 and l2 are connected together end to end, the result is a body of length l1 C l2.A similar relationship exists between separate masses and separate times. However, if two bodies at the same temperature are connected together, the joined body has the same temperature as each of the original bodies. This is a root cause of the fundamental difficulties that exist in establishing an absolute standard for temperature in the form of a relationship between it and other measurable quantities for which a primary standard unit exists. In the absence of such a relationship, it is necessary to establish fixed, reproducible reference points for temperature in the form of freezing and boiling points of substances where the transition between solid, liquid and gaseous states is sharply defined. The International Practical Temperature Scale (IPTS)Ł uses this philosophy and defines six primary fixed points for reference temperatures in terms of: ž the triple point of equilibrium hydrogen 259.34°C ž the boiling point of oxygen 182.962°C ž the boiling point of water 100.0°C ž the freezing point of zinc 419.58°C ž the freezing point of silver 961.93°C ž the freezing point of gold 1064.43°C (all at standard atmospheric pressure) The freezing points of certain other metals are also used as secondary fixed points to provide additional reference points during calibration procedures. -
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. -
Thermocouple Wire Alumel KN
Thermocouple wire Alumel®KN Alumel®KN - nickel-based alloy, alloyed with aluminum, silicon, manganese and cobalt. What is more, cobalt is present as impurity at nickel, and for ensuring the required value of Seebeck EMF his contents has to be within 0,6-1,0%. Alumel®KN is being used in pyrometry for production of compensating wires and also in the form of a negative thermoelectrode for production of thermocouples. Thermocouples with Alumel®KN is using for changing temperature up to 1000 °С. After Seebeck EMF stabilizing, it is possible to use thermocouple at temperature up to 1300°С. Classification MAIN DELIVERY CONDITIONS DIN 2.4122 Alumel®KN alloy is supplied in shape of strip or wire. Abbr. KN/KNX Alumel®KN wire, price of which depends on nickel and aluminum prices, is demanded in the industry at production of thermocouples and compensation Chemical composition, % wires. Ni+Co Fe C Mn Si P S Supplied together with alloy СгоmеІ®КР 91.5-95.15 ≤0.3 ≤0.1 1.8-2.7 0.85-1.5 ≤0.005 ≤0.010 Co Al Cu As Pb Mg Sb Wire 0.6-1.2 1.6-2.4 ≤0.25 ≤0.002 ≤0.002 ≤0.05 ≤0.002 Alumel®KN is supplied with diameters from 0,0254 to 8,0 mm. Wire Alumel®KN with sizes from 0,0254 mm to 0,51 mm can be supplied with insulated coating or PHYSICAL PROPERTIES 3 without it. Density, g/cm 8,67 Melting point, °С 1440 Strip TCLE, mm/m·°С (from 20° to 100°С) 18,0 Standard sizes of Alumel®KN strip are next: thickness Electrical resistance, μΩm 0,33 from 0.1 to 3.0 mm, width from 4 to 195 mm. -
Elastic Plastic Fracture Toughness of Aluminium Alloy AA6061 Fly Ash Composites
Research Article Adv. Mat. Lett. 2014, 5(9), 525-530 ADVANCED MATERIALS Letters www.amlett.com, www.vbripress.com/aml, DOI: 10.5185/amlett.2014.5571 Published online by the VBRI press in 2014 Elastic plastic fracture toughness of aluminium alloy AA6061 fly ash composites Ajit Bhandakkar1*, R. C. Prasad1, Shankar M. L. Sastry2 1Department of Metallurgical Engineering and Materials Science, IIT Bombay, India 2Mechanical, Aerospace and Structural Engineering, Washington University in St. Louis, USA *Corresponding author. Tel: (+91) 9422247576: E-mail: [email protected] Received: 07 January 2014, Revised: 23 June 2014 and Accepted: 28 June 2014 ABSTRACT Aluminium fly ash metal matrix composites (MMCs) find important applications in aerospace and automobiles where specific stiffness is important. Low cost fly ash and silicon carbide reinforcement are widely used in aluminium metal and matrix composite due to its low density, high young modulus and strength apart from good mechanical and chemical compatibility & thermal stability. However the MMCs often suffer from low ductility, toughness and fatigue crack growth resistance relative to the matrix alloy. Linear elastic fracture mechanics (LEFM) has been used to characterize the plane strain fracture toughness using various specimen geometries and notches but very few studies using EPFM are reported in literature. In the present paper the influences of weight fraction of particulate reinforcement on tensile, fracture toughness have been evaluated. The tensile strength of aluminium fly ash composites increases with the addition of fly ash reinforcement. However the fracture toughness (KIC) of the aluminium fly ash composite decreases that of base alloy. The fracture toughness KQ of AA6061 ALFA composites varied between 13-14 MPa as compared to 18 MPa for the re-melted base alloy. -
ILC Space Suits & Related Products
ILC Space Suits & Related Products 0000-712731 Rev. A REVISIONS LETTER DESCRIPTION DATE - Initial Release 10/26/07 A Update with review comments and inclusion of the Antarctic Habitat and 11/28/07 Shuttle Adjustable Protective Mitten Assembly (APMA). This report was written through the volunteer efforts of ILC employees, retirees and friends. Additionally, this report would not have been possible without the efforts of Ken Thomas at Hamilton Sundstrand who truly realizes the significance of preserving the history of US space suit development. The information has been compiled to the best of the participant’s abilities given the volunteer nature of this effort. Any errors are unintentional and will be corrected once identified and verified. If there are any questions regarding any detail of this report, please call (302) 335-3911 Ext. 248. The production of this report does not imply ILC Dover agrees with or is responsible for the contents therein. This report has been compiled from information in the public domain and poses no export licensing issues. William Ayrey Primary Author & Publisher 2 ILC Space Suits & Related Products 0000-712731 Rev. A Table Of Content Chapter 1 The Path Leading To Space -------------------------------------------------------------------------------- 6 The XMC-2-ILC X-15 Competition Prototype (1957) --------------------------------------------------------- 6 The SPD-117 Mercury Competition Prototype (1959) --------------------------------------------------------- 8 Chapter 2 The Journey To The Moon (1960-72) --------------------------------------------------------------- 9 ILC Developments & Prototype Suits Leading To The Apollo Contract (1960-62)----------------------- 10 SPD-143 Training Suits -------------------------------------------------------------------------------------------- 14 Glove Development For Apollo And The World (1962-Present) -------------------------------------------- 17 AX1H - The First New Design Of The Apollo Program ------------------------------------------------------ 19 AX2H Suits (Sept. -
Research of Combined Rolling-Extrusion Process for Production of Long Deformed Semi-Finished Products from Aluminium Alloys of Various Alloying Systems
RESEARCH OF COMBINED ROLLING-EXTRUSION PROCESS FOR PRODUCTION OF LONG DEFORMED SEMI-FINISHED PRODUCTS FROM ALUMINIUM ALLOYS OF VARIOUS ALLOYING SYSTEMS TABLE OF CONTENTS 1. CURRENT STATUS AND DEVELOPMENT TRENDS OF TECHNOLOGIES AND EQUIPMENT FOR COMBINED PROCESSING OF ALUMINIUM ALLOYS 1.1. METHODS AND TECHNOLOGIES FOR CONTINUOUS PROCESSING OF ALUMINIUM ALLOYS 1.2 ANALYSIS OF RESEARCH RESULTS FOR IDENTIFICATION OF DEFORMATION AND POWER PARAMETERS IN COMBINATION OF ROLLING AND EXTRUSION 1.3 SELECTION OF MATERIALS FOR RESEARCH 1.4. CONCLUSIONS AND SETTING OF OBJECTIVES 2. SIMULATION AND ANALYTICAL STUDIES OF COMBINED ROLLING- EXTRUSION OF ALLUMINIUM ALLOYS 2.1. SIMULATION OF COMBINED ROLLING-EXTRUSION PROCESS 2.2. RESEARCH OF GEOMETRICAL SHAPE OF DEFORMATION ZONE AND FEASIBILITY OF ROLLING-EXTRUSION PROCESS 2.3. CHARACTERIZATION OF RHEOLOGICAL PROPERTIES OF EXPERIMENTAL ALUMINIUM ALLOYS 2.4. CALCULATION OF POWER PARAMETERS OF ROLLING-EXTRUSION 3. EXPERIMENTAL RESEARCH OF COMBINED ROLLING-EXTRUSION PROCESS 3.1 DESCRIPTION OF EQUIPMENT AND METHODS OF EXPERIMENTAL RESEARCH 3.2. RESULTS OF EXPERIMENTAL RESEARCH AND THEIR ANALYSIS 3.3. RESEARCH OF STRUCTURE AND PROPERTIES OF PRODUCTS MADE BY CRE (COMBINED ROLLING-EXTRUSION) METHOD OF EXPERIMENTAL ALLOYS 3.4. PRACTICAL APPLICATION OF RESEARCH RESULTS CONCLUSION REFERENCE LIST 2 INTRODUCTION High production volumes of long-length deformed semi-finished products of relatively small cross-section made of aluminum and its alloys (wire rods, bars and wire) have conditioned the creation of new technologies of combined processing with the use of continuous methods of casting and basic metal-forming operations which for production of the above-mentioned products are advisable to be applied as rolling and extrusion [1-4]. -
Application of Thin-Fih Thermocouples to Localized Heat Transfer Measurements
Application of Thin-Fih Thermocouples to Localized Heat Transfer Measurements J. ~epicovsky* NXWA, Inc., Brook Park, OH 44142 and R. J. Brucknert and F .A. Smith NASA Lewis Research Center, Cleveland, OH 44135 The paper describes a proof-of-conceptexperiment on thin-fh thermocouples used for localized heat transfer measurements applicable to experiments on hot parts of turbine engines. The paper has three main parts. The fwst part describes the thm-fh sensors and manufacturing procedures. Attention is paid to connections between thm-film thermocouples and lead wires, which has been a source of problems in the past. The second part addresses the test arrangement and facility used for the heat transfer measurements modeling the conditions for upcoming warm turbine tests at NASA LeRC. The paper stresses the advantages of a modular approach to the test rig design. Finally, we present the results of bulk and local heat flow rate measurements, as well as overall heat transfer coefficients obtained from measurements in a narrow passage with an aspect ratio of 11.8. The comparison of bulk and local heat flow rates confm applicability of thin-film thermocouples to upcoming warm turbine tests. List of Symbols Reynolds number, coolant side, Efficient turbine blade cooling in high performance at the entrance to the cooling jet engines, coupled with minimum requirements on the passage amount of cooling air, has recently become a critical Reynolds number, hot-gas side, issue in engine developments. Local hot spots on the at the centerline of the test blades, which may form due to non-unifom cooling, module can impose severe limitations on an engine's local heat flow rate performance and structural integrity.