METAL SOLUTIONS

EOS NickelAlloy IN718

Material Data Sheet | Powder Product No. 9011-0020 / 9030-0022

EOS NickelAlloy IN718

High Temperature Strength and Corrosion Resistance

EOS NickelAlloy IN718 is a precipitation-hardening nickel-chromium alloy that is characterized by having good tensile, fatigue, creep and rupture strength at temperatures up to 700 °C (1290 °F). Parts built from EOS NickelAlloy IN718 can be easily post-hardened by precipitation-hardening heat treatments.

EOS NickelAlloy IN718 is a nickel alloy powder intended for manufacturing parts on EOS metal systems with EOS DMLS processes.

MAIN CHARACTERISTICS

  • Good tensile, fatigue, creep and rupture strength at temperatures up to 700 °C (1 290 °F)
  • Parts are easily precipitation hardened
  • Parts can be machined, spark-eroded, welded, micro shot-peened, polished and coated in both as-built and age-hardened states
  • Available in 10 kg drum and 500 kg Big Bag packaging 

Download Process Data Sheet (PDF)

TYPICAL APPLICATIONS

  • Gas turbine components
  • Instrumentation parts
  • Power industry parts
  • Process industry parts

The EOS Quality Triangle

Material Data Sheet | Powder Product No. 9011-0020 / 9030-0022
EOS uses an approach that is unique in the AM industry, taking each of the three central technical elements of the production process into account: the system, the material and the process. The data resulting from each combination is assigned a Technology Readiness Level (TRL) which makes the expected performance and production capability of the solution transparent.

EOS incorporates these TRLs into the following two categories:
 
  • Premium products (TRL 7-9): offer highly validated data, proven capability and reproducible part properties. 
  • Core products (TRL 3 and 5): enable early customer access to newest technology still under development and are therefore less mature with less data.

All of the data stated in this material data sheet is produced according to EOS Quality Management System and international standards
EOS 3D Printing Solutions Quality Triangle

POWDER PROPERTIES

The chemical composition of EOS NickelAlloy IN718 is in compliance with UNS N07718, AMS 5662, AMS 5664, W.Nr 2.4668, DIN NiCr19Fe19NbMo3.

Powder Chemical Composition (wt.-%)

Element Min. Max.
Fe Balance
Ni 50 55
Cr 17 21
Nb 4.75 5.5
Mo 2.8 3.3
Ti 0.65 1.15
Al 0.2 0.8
Co 0 1
Cu 0 0.3
Si 0 0.35
Mn 0 0.35
Ta 0 0.05
C 0 0.08
S 0 0.015
P 0 0.015
B 0 0.006
Pb 0 0.0005
Se 0 0.002
Bi 0 0.00003

Powder Particle Size

Generic Particle Size Distribution 20 - 55 µm

SEM micrograph of EOS NickelAlloy IN718 powder

HEAT TREATMENT

Description

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ“). Heat treatment is also used to relieve stresses

Steps

Step 1: Solution Annealing: hold at 954 °C (1 750 °F ) for 1 hour per 25 mm (0.98 inch) of thickness, air (/argon) cool

Step 2: Ageing Treatment: hold at 718 °C (1 325 °F ) 8 hours, furnace cool to 621 °C (1 150 °F ) and hold at 621 °C (1 150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Process Data Sheet

EOS NickelAlloy IN718 for EOS M 400 | 40 µm

EOS M 400 - 40 µm - TRL 7

System Setup EOS M 400
EOS Material set IN718_040_FlexM400
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.5 or newer
Recoater Blade HSS (High Speed Steel)
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 µm
Volume Rate 4.2 mm³/s

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm 0.02 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 40 µm ≥ 8.15 g/cm³ -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1150 1420 16 - - -
Horizontal 1240 1510 14 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1: 
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2: 
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 650 1000 29 - - -
Horizontal 780 1090 24 - - -

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 400-4 | 40 µm

EOS M 400-4 - 40 µm - TRL 7

System Setup EOS M 400-4
EOS Material set IN718_040_FlexM404
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.0 or newer
Recoater Blade HSS (High Speed Steel)
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 µm
Volume Rate up to 4 x 4.2 mm³/s
Min. Wall Thickness typical 0.3 - 0.4 mm

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm 0.04 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 40 µm ≥ 8.15 g/cm³ -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1220 1420 16 - - -
Horizontal 1300 1510 15 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1: 
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2: 
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) 4.5 -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 290 | 40 µm

EOS M 290 - 40 µm - TRL 9

System Setup EOS M 290
EOS Material set IN718_040_PerformanceM291
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 1.7 or newer

EOSPRINT 2.6 or newer and EOSYSTEM 2.9 or newer
Recoater Blade HSS (High Speed Steel)
Nozzle EOS Grid Nozzle
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 µm
Volume Rate 4.2 mm³/s
Min. Wall Thickness 0.3 - 0.4 mm

Chemical and Physical Properties of Parts

Heat treated microstructure. Etched according to ASTM E407-07.

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm 0.03 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 40 µm ≥ 8.15 g/cm³ -

Mechanical Properties Heat Treated

Room Temperature | Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1145 1375 17 - - -
Horizontal 1240 1505 12 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1: 
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2: 
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 650 970 32 - - -
Horizontal 800 1090 25 - - -

Hardness

Heat Treated
Value 47
Unit HRC
Heat Treated
Value 466
Unit HB

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
The surface quality was characterized by optical measurement method according to internal procedure. The 90 degree angle corresponds to vertical surface.

Coefficient of Thermal Expansion

Temperature
13.1*10-6/K 25 – 100 ºC
13.7*10-6/K 25 – 200 ºC
14.1*10-6/K 25 – 300 ºC
14.4*10-6/K 25 – 400 ºC
14.7*10-6/K 25 – 500 ºC
15*10-6/K 25 – 600 ºC
15.5*10-6/K 25 – 700 ºC
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 300-4 | 40 µm

EOS M 300-4 - 40 µm - TRL 3

System Setup EOS M 300-4
EOS Material set IN718_040_CoreM304
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.9 or newer
EOSYSTEM 2.12 or newer
Recoater Blade HSS (High Speed Steel)
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 µm
Volume Rate up to 4 x 4.2 mm³/s

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm < 0.05 % -

Mechanical Properties

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 635 955 36 - - -
Horizontal 795 1090 27 - - -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1140 1370 20 - - -
Horizontal 1270 1530 15 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1:
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2:
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 300-4 | 80 µm HiPro

EOS M 300-4 - 80 µm - TRL 5

System Setup EOS M 300-4
EOS Material set IN718_080_HiProM304
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.11 or newer
EOSYSTEM 2.15 or newer
Recoater Blade HSS (High Speed Steel)
Inert gas Argon
Additional Information
Layer Thickness 80 µm
Volume Rate up to 4 x 9.9 mm³/s
Min. Wall Thickness 0.3 - 0.4 mm

Chemical and Physical Properties of Parts

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 80 µm 0.03 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 80 µm ≥ 8.15 g/cm³ -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 80 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1190 1440 16 - - -
Horizontal 1240 1500 13 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1:
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2:
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 620 1070 26 - - -
Horizontal 760 1000 33 - - -

Hardness

EN ISO 6507 Heat Treated
Value 456
Unit HV

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 400-4 | 40 µm HiPro

EOS M 400-4 - 40 µm - TRL 5

Process Information Metal

This process parameter includes two variations of the exposure set: the first one provides better productivity while the second one enables low angle buildability down to 20°. The low angle buildability can be optimized further through the part geometry and the length of overhang.

System Setup EOS M 400-4
EOS Material set IN718_040_080_HiProM404
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.11 or newer

EOSYSTEM 2.15 or newer
Recoater Blade HSS (High Speed Steel)
Nozzle EOS Aerospike Nozzle
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 µm
Volume Rate up to 4 x 5.2 mm³/s
Min. Wall Thickness typical 0.3 - 0.4 mm

Chemical and Physical Properties of Parts

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm 0.01 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 40 µm ≥ 8.21 g/cm³ -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1170 1410 15 - - -
Horizontal 1240 1490 13 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1:
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2:
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Tensile properties at elevated temperatures

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 630 970 30 - - -
Horizontal 770 1060 26 - - -

Hardness

EN ISO 6507 Heat Treated
Value 463
Unit HV
ASTM E292 Heat Treated Stress [MPa] Temperature [°C] Time to Rupture
[hrs] Elongation
[%] RA
[%]
Vertical 689 650 53 5 20.05

The stress-rupture performance of EOS NickelAlloy IN718 was tested on vertically oriented samples, in heat-treated condition. No HIP was applied. The data presents the Larson-Miller parameter values achieved at stress levels of 689 MPa. 

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 400-4 | 80 µm HiPro

EOS M 400-4 - 80 µm - TRL 7

Process Information Metal

This process provides high productivity with a volume rate that is 119% faster than the IN718 40 µm Flexline and 77% faster than IN718 40 µm HiPro processes.

System Setup EOS M 400-4
EOS Material set IN718_040_080_HiProM404
Powder Product No. 9011-0020 / 9030-0022
Software Requirements

EOSPRINT 2.11 or newer
EOSYSTEM 2.15 or newer
Recoater Blade HSS (High Speed Steel)
Nozzle EOS Aerospike Nozzle
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 80 µm
Volume Rate up to 4 x 9.2 mm³/s
Min. Wall Thickness 0.3 - 0.4 mm

Chemical and Physical Properties of Parts

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 80 µm 0.025 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 80 µm ≥ 8.25 g/cm³ -

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1200 1430 13 - - -
Horizontal 1250 1500 12 - - -

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1:
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2:
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Tensile properties at elevated temperatures

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 80 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 630 980 29 - - -
Horizontal 750 1060 25 - - -
ASTM E292 Heat Treated Stress [MPa] Temperature [°C] Time to Rupture
[hrs] Elongation
[%] RA
[%]
Vertical 689 650 56 9 20.07

The stress-rupture performance of EOS NickelAlloy IN718 was tested on vertically oriented samples, in heat-treated condition. No HIP was applied. The data presents the Larson-Miller parameter values achieved at stress levels of 689 MPa. 

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
Process Data Sheet

EOS NickelAlloy IN718 for EOS M 290 | 40 & 80 µm

EOS M 290 - 40 um

Process Information Metal

The material set enables processing of EOS NickelAlloy IN718 in 40 μm and 80 μm layer thicknesses using argon as inert gas. This set is a major overhaul of IN718_040_080_HiProM291 1.03 with new exposure options with improved low angle buildability and changed 40 μm exposure.
The exposure sets included are:
“EOS_Part” is the classic 40 μm set familiar from IN718_040_PerformanceM291 2.13. Full datasheet available here. 
“EOS_Part_Fast” is the 80 μm set familiar from IN718_040_080_HiProM291 1.03.
“EOS_Part_LowAngle” presents a new exposure set with highly improved buildability of low angles with good surface roughness in 40 μm.
“EOS_Part_Fast_LowAngle” presents a new exposure set with highly improved buildability of low angles with good surface roughness in 80 μm.

System Setup EOS M 290
Powder Product No. 9011-0020 / 9030-0022
Recoater Blade HSS (High Speed Steel)
Nozzle EOS Grid Nozzle
Inert gas Argon
Sieve 63 µm
Additional Information
Layer Thickness 40 um, 80 µm
Volume Rate 4.6 / 8.2 mm³/s
Min. Wall Thickness Typical 0.3 - 0.4 mm mm

Chemical and Physical Properties of Parts

Microstructure of the Produced Parts

Defects Thickness Result Number of Samples
Average Defect Percentage 40 µm 0.01 % -
Average Defect Percentage 80 µm 0.03 % -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 40 µm ≥ 8.15 g/cm³ -
Density EN ISO 3369 Thickness Result Number of Samples
Average Density 80 µm ≥ 8.15 g/cm³ -

Mechanical Properties

Mechanical Properties Heat Treated

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1190 1390 15 - - -
Horizontal 1270 1530 17 - - -

The data has been generated with the exposure set "EOS_Part_LowAngle". See release note for details. 

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1: 
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2: 
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Mechanical Properties As Manufactured

EN ISO 6892-1 Room Temperature | 40 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 660 970 33 - - -
Horizontal 190 170 27 - - -

The data has been generated with the exposure set "EOS_Part_LowAngle". See release note for details. 

Mechanical Properties Heat Treated

EN ISO 6892-1 Method A, Range 1 (0.00007 1/s) Room Temperature | 80 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 1200 1440 16 - - -
Horizontal 1230 1490 14 - - -

The data has been generated with the exposure set "EOS_Part_Fast_LowAngle". See release note for details.

Heat treatment procedure conform to Aerospace Material Specification AMS 2774 and AMS 5662. 
As manufactured microstructure for additively manufactured IN718 consists of gamma phase (γ). Heat treatment for IN718 is required to produce desired microstructure and part properties (gamma double prime precipitates, γ"). Heat treatment is also used to relieve stresses.

Step 1:
Solution Anneal: hold at 954 °C (1750 °F ) for 1 hour per 25mm (0.98 inch) of thickness, air (/argon) cool

Step 2:
Ageing treatment; hold at 718 °C (1325 °F ) 8 hours, furnace cool to 621 °C (1150 °F ) and hold at 621 °C (1150 °F ) for total precipitation time of 18 hours, air (/argon) cool

Mechanical Properties As Manufactured

EN ISO 6892-1 Method A, Range 1 (0.00007 1/s) Room Temperature | 80 µm Yield Strength [MPa] Tensile Strength [MPa] Elongation at Break A [%] Reduction of Area Z [%] Modulus of elasticity [GPa] Number of Samples
Vertical 640 980 32.5 - - -
Horizontal 740 1040 29 - - -

The data has been generated with the exposure set "EOS_Part_Fast_LowAngle". See release note for details.

Surface Roughness

Surface Roughness From To
Sa (µm) - -
Ra (µm) - -
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