5 Years manufacturer D2 Tool Steel | 1.2379 | X153CrMo12 | SKD11 Manufacturer in Sri Lanka

5 Years manufacturer
 D2 Tool Steel | 1.2379 | X153CrMo12 | SKD11 Manufacturer in Sri Lanka

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1. Relevant D2 Steel Specifications Country USA German Japan Standard ASTM A681 DIN EN ISO 4957 JIS G4404 Grades D2 1.2379/X153CrMo12 SKD11 2. D2 Tool Steel Chemical Composition ASTM A681 C Mn P S Si Cr V Mo D2 1.4 1.6 0.1 0.6 0.03 0.03 0.1 0.6 11 13 0.5 1.1 0.7 1.2 DIN ISO 4957 C Mn P S Si Cr V Mo 1.2379/X153CrMo12 1.45 1.6 0.2 0.6 0.03 0.03 0.15 1.6 11 13 0.7 1 0.7 1 JIS G4404 C Mn P S Si Cr V Mo SKD11 1.4 1.6 0.6 0.03 0.03 0.4 11 13 0.2 0.5 0.8 1.2 3. AISI Grade...

  • Length: 3-5.8mm or Customization
  • Surface: black, peeled, or rough turned
  • Heat treatment: air-cooling, normalized, annealed, Q&T
  • Smelting process: EAF+LF+VD
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    1. Relevant D2 Steel Specifications

    Country USA German Japan
    Standard ASTM A681 DIN EN ISO 4957 JIS G4404
    Grades D2 1.2379/X153CrMo12 SKD11

    2. D2 Tool Steel Chemical Composition

    ASTM A681 C Mn P S Si Cr V Mo
    D2 1.4 1.6 0.1 0.6 0.03 0.03 0.1 0.6 11 13 0.5 1.1 0.7 1.2
    DIN ISO 4957 C Mn P S Si Cr V Mo
    1.2379/X153CrMo12 1.45 1.6 0.2 0.6 0.03 0.03 0.15 1.6 11 13 0.7 1 0.7 1
    JIS G4404 C Mn P S Si Cr V Mo
    SKD11 1.4 1.6 0.6 0.03 0.03 0.4 11 13 0.2 0.5 0.8 1.2

    3. AISI Grade D2 Steel Mechanical Properties

    Mechanical Properties Metric Imperial
    Hardness, Knoop (converted from Rockwell C hardness) 769 769
    Hardness, Rockwell C 62 62
    Hardness, Vickers 748 748
    Izod impact unnotched 77.0 J 56.8 ft-lb
    Poisson’s ratio 0.27-0.30 0.27-0.30
    Elastic modulus 190-210 GPa 27557-30457 ksi

    Thermal Properties



    T (°C)


    Thermal expansion 10.4 x 10-6/ºC 20-100

    4. AISI/ASTM A681 D2 Grade Steel Forging

    Heating for forging of AISI D2 tool steel should
    be done slowly and uniformly. Soak through at 1850°-1950°F and reheat as often
    as necessary, stopping work when the temperature drops below 1700°F(926℃). After D2
    die steel forging, cool slowly in lime, mica, dry ashes or furnace. AISI D2 steel
    should always be annealed after forging.

    5. D2 Tool Steel Heat Treatment

    • Heat Treatment

    ASTM  D2 steels alloy should be preheated very slowly to 815oC (1500oF) and  then temperature can be increased to 1010oC (1850oF). They are then held  at 1010oC (1850oF) for 20 to 45 minutes and air cooled (air quenched).

    • Annealing

    Annealing  of D2 tool steels material should be done at 871 to 898oC (1600 to  1650oF) followed by slow furnace cooling at 4.4oC (40oF) per hour or  less.after which cooling rate may be increased. Suitable precautions  must be taken to prevent excessive carburization or decarburization.

    • Stress Relieving

    When  desirable to relieve the strains of machining, heat D2 grade steel  slowly to 1050°-1250°F, allow to equalize, and then cool in still air  (Strain Relieving).

    • Preheat Prior To Hardening

    Preheat slowly to 1350°-1450°F and hold at this temperature until grade steel D2 material is uniformly heated.

    • Hardening

    After  thorough preheating, heat to 1800°-1850°F. Hold the work piece at the  hardening temperature until it is completely and uniformly heated.

    • Quenching

    AISI  D2 steel tool material is an air hardening steel and will develop  hardness on cooling in still air. To avoid scaling and prevent  decarburization of the work piece surface, controlled atmosphere or  vacuum furnaces are recommended. If these furnaces are not available,  pack hardening, salt baths or wrapping the piece in stainless steel foil  will provide some degree of surface protection in the hardening  process. Parts should be allowed to cool to 150F, or to where they can  be held in the bare hand, and then temper immediately.

    • Tempering

    The  tempering temperature on material D2 steel may be varied according to  the desired hardness. D2 steels can be tempered at 204oC (400oF) for  achieving Rockwell C hardness of 61 and at 537oC (1000oF) for a Rockwell  C hardness of 54.

    6. D2 Tool Steel Material Application
     AISI grade D2 tool steels are used for long run tooling applications,  where wear resistance is important, such as blanking or forming dies and  thread rolling dies.

    Some main applications for D2 tool steel are as below:

    Blanking  Dies, Forming Dies, Coining Dies, Slitting Cutters, Heading Tools, Long  Punches, Forming Rolls, Edging Rolls, Master Tools, Beading Rolls,  Intricate Punches, Extrusion Dies, Drawing Dies, Lamination Dies, Thread  Rolling Dies, Shear Blades, Burnishing Tools, Gauges, Knurls, Wear  Parts.

    We usually hold D2 tool  steel on sale activities, and you would have our price on regular  schedule. Contact us and sign in our newsletter to have D2 tool steel  materials price list and commercial quote today.

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    Chemical Properties of Metals

    A metal is a chemical element that is a good conductor of both electricity and heat and forms cations and ionic bonds with non-metals. In chemistry, a metal ( from Greek “μέταλλον” – métallon, “mine”) is an element, compound, or alloy characterized by high electrical conductivity. In a metal, atoms readily lose electrons to form positive ions (cations). Those ions are surrounded by delocalized electrons, which are responsible for the conductivity. The solid thus produced is held by electrostatic interactions between the ions and the electron cloud, which are called metallic bonds.
    Chemical properties of metals
    Metals are usually inclined to form cations through electron loss,reacting with oxygen in the air to form oxides over changing timescales (iron rusts over years, while potassium burns in seconds). Examples:
    4 Na + O2 → 2 Na2O (sodium oxide)
    2 Ca + O2 → 2 CaO (calcium oxide)
    4 Al + 3 O2 → 2 Al2O3 (aluminium oxide)
    The transition metals (such as iron, copper, zinc, and nickel) take much longer to oxidize. Others, like palladium, platinum and gold, do not react with the atmosphere at all. Some metals form a barrier layer of oxide on their surface which cannot be penetrated by further oxygen molecules and thus retain their shiny appearance and good conductivity for many decades (like aluminium, some steels, and titanium). The oxides of metals are generally basic, as opposed to those of nonmetals, which are acidic.
    Painting, anodizing or plating metals are good ways to prevent their corrosion. However, a more reactive metal in the electrochemical series must be chosen for coating, especially when chipping of the coating is expected. Water and the two metals form an electrochemical cell, and if the coating is less reactive than the coatee, the coating actually promotes corrosion.

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    “This film is from Lewis Flight Propulsion Laboratory, now known as NASA Glenn Research Center. The film looks at addressing the problem of turbine inlet temperature and the benefits of air-cooled blades. A promising blade is the fabrication of cast air-cooled blades using a lost wax technique. Video is in color and has sound.”

    Langley Film L-708

    Public domain film from NASA, slightly cropped to remove uneven edges, with the aspect ratio corrected, and mild video noise reduction applied.
    The soundtrack was also processed with volume normalization, noise reduction, clipping reduction, and equalization.


    A turbine blade is the individual component which makes up the turbine section of a gas turbine. The blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor. The turbine blades are often the limiting component of gas turbines. To survive in this difficult environment, turbine blades often use exotic materials like superalloys and many different methods of cooling, such as internal air channels, boundary layer cooling, and thermal barrier coatings.

    In a gas turbine engine, a single turbine section is made up of a disk or hub that holds many turbine blades. That turbine section is connected to a compressor section via a shaft (or “spool”), and that compressor section can either be axial or centrifugal. Air is compressed, raising the pressure and temperature, through the compressor stages of the engine. The pressure and temperature are then greatly increased by combustion of fuel inside the combustor, which sits between the compressor stages and the turbine stages. That high temperature and high pressure fuel then passes through the turbine stages. The turbine stages extract energy from this flow, lowering the pressure and temperature of the air, and transfer that energy to the compressor stages along the shaft. This is process is very similar to how an axial compressor works, only in reverse.

    The number of turbine stages varies in different types of engines, with high thrust, high bypass ratio, engines tending to have the most turbine stages.[citation needed] The number of turbine stages can have a great effect on how the turbine blades are designed for each stage. Many gas turbine engines are two shaft designs, meaning that there is a high pressure shaft and a low pressure shaft. Other gas turbines used three shafts, adding an intermediate pressure shaft between the high and low pressure shafts. The high pressure turbine is exposed to the hottest, highest pressure, air, and the low pressure turbine is subjected to cooler, lower pressure air. That difference in conditions leads the design of high pressure and low pressure turbine blades to be significantly different in material and cooling choices even though the aerodynamic and thermodynamic principles are the same.

    Turbine blades are subjected to very strenuous environments inside a gas turbine. They face high temperatures, high stresses, and a potentially high vibration environment. All three of these factors can lead to blade failures, which can destroy the engine, and turbine blades are carefully designed to resist those conditions.

    Turbine blades are subjected to stress from centrifugal force (turbine stages can rotate at tens of thousands of revolutions per minute (RPM) and fluid forces that can cause fracture, yielding, or creep failures. Additionally, the first stage (the stage directly following the combustor) of a modern turbine faces temperatures around 2,500 °F (1,370 °C), up from temperatures around 1,500 °F (820 °C) in early gas turbines. Modern military jet engines, like the Snecma M88, can see turbine temperatures of 2,900 °F (1,590 °C)…

    A key limiting factor in early jet engines was the performance of the materials available for the hot section (combustor and turbine) of the engine. The need for better materials spurred much research in the field of alloys and manufacturing techniques, and that research resulted in a long list of new materials and methods that make modern gas turbines possible.. One of the earliest of these was Nimonic, used in the British Whittle engines.

    The development of superalloys in the 1940s and new processing methods such as vacuum induction melting in the 1950s greatly increased the temperature capability of turbine blades. Further processing methods like hot isostatic pressing improved the alloys used for turbine blades and increased turbine blade performance.[6] Modern turbine blades often use nickel-based superalloys that incorporate chromium, cobalt, and rhenium.

    Aside from alloy improvements, a major breakthrough was the development of directional solidification (DS) and single crystal (SC) production methods…

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