Additive manufacturing
A method of additive manufacturing metallic components, the method includes: forming a component in a layer by layer process, the component being formed integrally with at least one non-perforated support structure to be separated from the component after the layer by layer process, the support structure being formed with at least one wall that is non-perforated; and wherein after completion of the layer by layer process, the method includes exposing the component and support structure to at least one thermal pulse so as to weaken, or break, the interface(s) between the support structure and component prior to removal of the support.
1. A method of additive manufacturing metallic components, the method comprising:
forming a component in a layer-by-layer process, the component being formed integrally with at least one non-perforated support structure to be separated from the component after the layer-by-layer process, the support structure being formed with at least one wall that is non-perforated; and
after completion of the layer-by-layer process, exposing the component and support structure to at least one thermal pulse so as to weaken, or break, an interface arranged between the support structure and component prior to removal of the support,
wherein the support structure is formed with a bulk support member, and wherein the interface is formed by a plurality of interface support members for connecting the bulk support member to the component,
wherein the width of the interface support members narrows from the bulk support member to the component,
wherein the thermal pulse is at a temperature exceeding the melting point of the metallic material,
wherein after mechanical removal of the support structure from the component, at least one further thermal pulse is applied to the separated component.
2. The method of claim 1 , wherein the support structure is formed with a plurality of walls.
3. The method of claim 2 , wherein a distance between each wall is at least 0.8 mm.
4. The method of claim 3 , wherein a centre-to-centre distance between each wall is at least 0.8 mm.
5. The method of claim 1 , wherein each of the walls is formed with a thickness of 0.1 mm or less.
6. The method according to claim 1 , wherein each interface support member is formed with its narrowest width at the interface with the component.
7. The method according to claim 6 , wherein each interface support member reaches its narrowest width at a predetermined distance away from the interface with the component, wherein the predetermined distance is between approximately 0.5 mm and approximately 2 mm away from the interface with the component.
8. The method according to claim 6 , wherein the interface support members have a base length defined as the length of the interface between the bulk support member and the interface support member, and ratio of the base length to a height of the interface support member is equal to 1.5 or less.
9. The method according to claim 6 , wherein: the component and support structure are formed on a baseplate;
the support structure comprises an internal support structure arranged between two parts of the component and an external support structure arranged between the component and the baseplate, the internal support structure and the external support structure both comprising a bulk support member and a plurality of interface support members;
the interface support members have a base length defined as the length of the interface between the bulk support member and the interface support member;
the base length to height ratio of the interface support members of the internal support structure is between 0.55 and 0.75; and
the base length to height ratio of the interface support members of the external support structure is between 1.2 and 1.4.
10. The method of claim 1 , wherein the step of exposing the component and support structure to a thermal pulse comprises placing the component and support structure in a chamber, filling the chamber with a combustible gas mixture, allowing the gas mixture to surround the component and support structure and igniting the gas mixture.
11. The method of claim 10 , wherein the thermal pulse is an explosive or pseudo-explosive combustion.
12. The method of claim 10 , wherein the chamber is at an increased atmospheric pressure of 400 bar and a peak pressure during combustion reaches 2000 bar or more.
13. The method of claim 1 , wherein a plurality of thermal pulses are applied to the separated metallic component.
14. The method of claim 1 , wherein the surface of the metallic component is abrasively cleaned after the application of at least one thermal pulse to the separated metallic component.
15. The method of claim 1 , wherein the additive manufacturing process comprises powder bed selective laser manufacturing.
16. The method of claim 1 , wherein the step of exposing the component and support structure to at least one thermal pulse provides a peak temperature increase of at least between approximately 2000° C. and approximately 3500° C.
17. The method of claim 1 , wherein the step of exposing the component and support structure to at least one thermal pulse comprises the thermal pulse having a duration between approximately 20 milliseconds and approximately 100 milliseconds.
18. A method of additive manufacturing metallic components, the method comprising:
forming a component in a layer-by-layer process, the component being formed integrally with at least one support structure to be separated from the component after the layer-by-layer process, the support structure being formed with at least one wall having a thickness of 0.1 mm or less; and
after completion of the layer-by-layer process, exposing the component and support structure to at least one thermal pulse so as to weaken, or break, an interface arranged between the support structure and component prior to removal of the support,
wherein after mechanical removal of the support structure from the component, at least one further thermal pulse is applied to the separated component.
19. A method of additive manufacturing metallic components, the method comprising:
forming a component in a layer-by-layer process, the component being formed integrally with at least one support structure to be separated from the component after the layer-by-layer process, the support structure being formed with a plurality of walls, wherein a distance between each wall is at least 0.8 mm; and
after completion of the layer-by-layer process, exposing the component and support structure to at least one thermal pulse so as to weaken, or break, an interface arranged between the support structure and component prior to removal of the support,
wherein after mechanical removal of the support structure from the component, at least one further thermal pulse is applied to the separated component.
20. The method of claim 19 , wherein each of the plurality of walls is non-perforated.
21. The method of claim 19 , wherein the plurality of walls are formed in a hatched arrangement.
22. The method according to claim 21 , wherein the plurality of walls are formed in a hatched arrangement fragmented into discrete smaller hatched sub-arrangements.