Factory wholesale C45 Round Bar | AISI 1045 | DIN 1.1191 | JIS S45C in Boston
Steel C45 Round Bar is an unalloyed medium carbon steel, which is also a general carbon engineering steel. C45 is a medium strength steel with good machinability and excellent tensile properties. C45 round steel is generally supplied in the black hot rolled or occasionally in the normalised condition, with a typical tensile strength range 570 – 700 Mpa and Brinell hardness range 170 – 210 in either condition. It does not however respond satisfactorily to nitriding due to a lack of suita...
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an unalloyed medium carbon steel, which is also a general carbon
engineering steel. C45 is a medium strength steel with good
machinability and excellent tensile properties. C45 round steel is
generally supplied in the black hot rolled or occasionally in the
normalised condition, with a typical tensile strength range 570 – 700
Mpa and Brinell hardness range 170 – 210 in either condition. It does
not however respond satisfactorily to nitriding due to a lack of
suitable alloying elements.
C45 round bar steel is equivalent to
Steel C45 bar or plate is suitable for the manufacture of parts such as
gears, bolts, general-purpose axles and shafts, keys and studs.
1. Supply Range of Steel C45 Round Bar
C45 Steel Round Bar: diameter 8mm – 3000mm
C45 Steel Plate: thickness 10mm – 1500mm x width 200mm – 3000mm
C45 Steel Flat Bar: 200mm – 1000mm
Square C45 Steel: 20mm-800mm
Surface Finish: Black, Rough Machined, Turned or as per given requirements.
2. Common C45 Steel Specifications
|Standard||EN 10083-2||AS 1442|
3. C45 Round Bar Steel Chemical Composition Properties
4. Mechanical Properties of C45 Round Bar Steel Material
Mechanical Properties in Quenched+Tempered Condition
|Diameter d (mm)||Thickness t (mm)||0.2 % proof stress (N/mm2)||Tensile strength (N/mm2)||Elongation A5 (%)||Reduction Z (%)|
|<16||<8||min. 490||700-850||min. 14||min. 35|
|<17-40||<8<=20||min. 430||650-800||min. 16||min. 40|
|<41-100||<20<=60||min. 370||630-780||min. 17||min. 45|
Mechanical Properties in Normalized Condition
|Diameter d (mm)||Thickness t (mm)||0.2 % proof stress (N/mm2)||Tensile strength (N/mm2)||Elongation A5(%)|
|<16||<16||min. 390||min. 620||min. 14|
|<17-100||<16<=100||min. 305||min. 305||min. 16|
|<101-250||<100<250||min. 275||min. 560||min. 16|
5. Forging of Carbon Steel C45 Round Bar
Hot forming temperature: 850-1200oC.
heat to 750 oC – 800 oC, then continue heating to 1100 oC – 1200 oC
maximum, hold until temperature is uniform throughout the section and
commence forging immediately. Forging is not workable below 850 oC.
Finished forgings could be air cooled.
We are strong on forged steel C45 round bar. Welcome enquiry of C45 steel materials.
6. DIN C45 Round Bar Steel Grade Heat Treatment
|Forging or hot rolling:||1100 – 850°C|
|Normalising:||840 – 880°C/air|
|Soft annealing:||680 – 710°C/furnace|
|Hardening:||820 – 860°C/water, oil|
|Tempering:||550 – 660°C/air|
7. Hardening of DIN C45 Steel Hardening
Harden from a temperature of 820-860oC followed by water or oil quenching.
to 820 oC – 850 oC hold until temperature is uniform throughout the
section, soak for 10 – 15 minutes per 25mm of section, and quench in
water or brine. Or,
Heat to 830 oC – 860 oC soak as above and quench in oil.Temper immediately while still hand warm.
Surface hardness for C45 special steel round bar after flame or induction hardning:
Steel Name Steel number Surface Harndess
C45 1.1191 min. 55 HRC
8. Application of DIN Carbon Steel C45 Round Bar
C45 round bar steel material and steel plate C45, flats are widely used
in all industry for uses which require more strength and wear
resistance than the low carbon mild steel.
subsequently tempered steel for C45 steel grade round bar, steel plate,
flat and square is used for axles, bolts, forged connecting rods,
crankshafts, torsion bars, light gears, guide rods, screws, forgings,
wheel tyres, shafts, sickles, axes, knives, wood working drills,
Welcome customers to inquiry DIN C45 round bar,
CK45/1.1191 steel plate, flat steel for C45 steel price. We are
professional supplier and exporter for more than 20 years. We offer you
worldwide solution for C45 round bar steel.
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Regarding the sanding block: lots of people asked about the sanding block I’m using, so I made a video about it here: http://www.youtube.com/watch?v=AtAZRdxUrh4
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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. 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. 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…