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Discover the variety

The range of our standard metallic materialsNon Ferrous Metals, Tool Steel, Stainless Steel and Light Alloys

Titanium

Titanium was first discovered in England in 1791. Approximately 150 years later and through the introduction of the Kroll-Process, titanium became a com-mercial product. Titanium (Ti) with the ordinal number 22 in the periodic system of elements is defined as a transi-tion metal. It is one of the most common elements on the earth`s surface and is lis-ted as the 10th most common element.

The material is particularly resistant to cor-rosion and with high mechanical proper-ties compared to the low specific weight. Pure titanium has a density of 4.54 g/cm3 with a melting point of 1677 centigrade.

Material StructureComponents produced by SLM in titanium show a homogenous, dense structure. If required, the structure can be heat treated to achieve the required shape.

Material Prosperties High strength at low density Corrosion resistance Bio-compatibility Low thermal expansion

Areas of Application Medizintechnik Aerospace Automotive Jewellery and Design Maritime applications

Alloys Pure titanium TiAl6Nb7 TiAl6V4

Other Materials on request.

Mechanical Data TiAl6V41 TiAl6Nb73 Reintitan1

Tensile strength Rm [MPa] 1286 57 > 972 > 290

Offset yield stress Rp0,2 [MPa] 1116 61 > 865 > 180

Break strain A [%] 8 2 > 10 > 20

Reduction of area Z [%] 30 10 - -

E-Module [GPa] 111 4 - 105

Hardness by Vickers [HV10] 384 5 360 130-210

Surface roughness Ra [ m ] - - -

Surface roughness RZ [ m ] 36 4 36 4 36 4

1 Layer thickness30 m without heat treatment 2 Layer thickness 50 m without heat treatment 3 Heat treated

Individual Hip Implantat in Titanium

Tool Steel and Stainless Steel

Going back two thousand years people were searching for cutting materials which were not only hard but also tough. Along with mass industrialisation at the beginning of the nine-teenth century the development of steel and its alloys materialised into what we now know as tool steel and stainless steel.

These materials reach a high skin hardness when heat treated, with a low carbon content of only 0,5 - 1,5 %.

Alloy constituents, when added can adjust the properties to an exact specification. Even corrosion resistant steels can be produced in the same way. These so called stainless steels are known for their low nitrogen and phos-phor content of less than 0.025% and today these materials are widely used in the mould making industry. Through the SLM Techno-logy the processing and extended application of these steel materials has been developed even further.

Material StructureComponents produced by SLM in steel show a homogenous, dense structure.

Due to the particularity of the SLM building process, levels of hardness can be achieved which cannot be equalled by conventio-nal heat treatment methods. Through post treatment, components can be brought to the condition required.

Material Prosperties Great hardness, good durability Corrosion resistance

Areas of Applications plastic injection and

pressure diecasting moulds maritime Applications Automotive

Alloys 1.2709 1.4404 (316L) 1.2344 (H13) 1.4540 (15-5PH) 1.4542 (17-4PH)

Other Materials on request.

Mechanical Data 1.4540 (15-5PH) 1 1.4404 (316L) 1 1.2344 (H13) 13 1.2709 13

Tensile strength Rm [MPa] 1100 50 654 49 1730 30 1015 34

Offset yield stress Rp0,2 [MPa] 1025 25 550 39 - 854 50

Break strain A [%] 16 4 35 4 - 10 1

Reduction of area Z [%] - 59 3 - 26 9

E-Modul [GPa] - 169 31 - 142 43

Hardness by Vickers [HV10] - 233 2 - 310 4

Surface roughness Ra [ m ] - 8 2 - 7 2

Surface roughness Rz [ m ] 14 2 40 11 34 4 39 8


Mould inserts with integrated, surface conformal cooling channels, Gardena AG

Aluminium

Aluminium (Al, ordinal number 13 in the periodic system of elements) belongs to the light metals group and cannot be found naturally in solid form. Aluminium is obtai-ned from bauxite. Bauxite is the third most common element on the earths surface.

Aluminium has a density of 2.7 g/cm3 and has a melting point of 660 centigrade. It can be processed relatively easily by cas-ting, machining and pressing. Due to its low strength it is used to produce alloys from silicon, magnesium, copper, manganese and zinc. Aluminium oxide (Al2O3) can also be found extensively as a ceramic.

Material StructureComponents produced by SLM in Aluminium show a homogenous, void free structure.

Due to the particularity of the SLM building process a typical hardness can be achieved. Through post treatment the components can be brought to the required condition.

Material Prosperties Low density Good alloying properties Good processability (casting and pressing etc.) Good electrical conductivity

Areas of Applications Automotive Aerospace Consumer goods

Alloys AlSi12 AlSi10Mg AlSi7Mg AlSi9Cu3 AlMg4,5Mn0,4 Other Materials on request.

Mechanical Data AlSi122 AlSi10Mg2 AlSi7Mg2

Tensile strength Rm [MPa] 409 20 397 11 294 17

Offset yield stress Rp0,2 [MPa] 211 20 227 11 147 15

Break strain A [%] 5,1 6 1 3,3

Reduction of area Z [%] - 8 1 -

E-Modul [GPa] - 64 10 -

Hardness by Vickers [HV10] 110 117 1 105

Surface roughness Ra [ m ] - - -

Surface roughness Rz [ m ] 34 4 - 31


Propeller for racing boats as scaled model for flow measurements

Cobalt-Chrome

Cobalt-Chrome alloys are standard alloys in the medical and dental fields.

Due to the high hardness, Cobalt-Chrome alloys are used to produce dental pros-theses. This is also influenced by the bio-compatibility of the alloy. Being a tough material, Cobalt-Chrome alloy is usually cast and not machined.

Other uses for Cobalt-Chrome are prosthesis and knee or and hip joint implants.

Material StructureComponents produced by SLM in cobalt-chrome alloys show homogenous and pore free structures.

Since CoCr is difficult to machine, the SLM process offers a quick and low cost method of producing components in these materials.

Material Prosperties Big toughness High strength Bio-compatibility Corrosion resistance

Areas of Applications Medical technology Dental technology High temperature

Mechanical Data CoCr1 (F75)

Tensile strength Rm [MPa] 1050 20

Offset yield stress Rp0,2 [MPa] 835 20

Break strain A [%] -

Reduction of area Z [%] -

E-Modul [GPa] -

Hardness by Vickers [HV10] 345

Surface roughness Ra [ m ] -

Surface roughness Rz [ m ] 29 4


Individual bridges and crowns in cobalt-chrome.

Nickel-base alloys

Developed in the early 1960s, IN718 is still considered the material of choice for the majority of aircraft engine components with service temperatures below 1200F (650C). Inconel 718 is a precipitation-hardenable nickel-chromium alloy containing also significant amounts of iron, niobium, and molybdenum along with lesser amounts of aluminum and titanium. It combines corro-sion resistance and high strength with out-standing weldability including resistance to postweld cracking. The alloy has excellent creep-rupture strength at temperatures to 1300F (700C).

Material Prosperties Corrosion resistance Excellent mechanical strength up to 700C Outstanding weldability

Anwendungsbereiche Aerospace Energy technology Toolmaking

Legierungen (Auswahl) Hastelloy X (2.4665) Inconel 625 Inconel 718 Inconel 939 Inconel 738

Mechanical Data Hastelloy X1 Inconel 6251 Inconel 7181 Inconel 9391

Tensile strength Rm [MPa] 772 24 961 41 995 43 1009 35

Offset yield stress Rp0,2 [MPa] 595 28 707 41 689 67 735 41

Break strain A [%] 20 6 33 2 29 4 30 4

Reduction of area Z [%] 21 7 51 5 47 4 45 7

E-Modul [GPa] 162 11 1829 173 17 177 8

Hardness by Vickers [HV10] 248 4 285 3 306 7 302 3

Surface roughness Ra [ m ] 8 3 - 6 2 -

Surface roughness Rz [ m ] 40 14 28 34 10 -


Turbine blade of latest generation with internal conformal cooling channels to improve performance of jet engines

slm-material engl

Documents

steel materials

titaniumtool steel

development of steel

phother materials

material structurecomponents

low nitrogen

stainless steels

high skin hardness