| 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
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 | - |