Turbine disk fabrication with in situ material property variation
AssigneeRaytheon Technologies Corporation
InventorsTahany Ibrahim El-Wardany, Matthew E. Lynch, Daniel V. Viens, Robert A. Grelotti
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Abstract
A method of fabricating a functionally graded turbine engine component is disclosed and includes the step of depositing layers of powder onto a base and solidifying/fusing each layer with a first directed energy beam to define a component. The method further includes varying a process parameter between deposited layers to define different material properties within the component. The method also proposes surface enhancement approach that can be used after depositing each layer to locally customize the material properties. The method also proposes machining the different internal surfaces to achieve the proper surface finishing required.
Claims15
A method of fabricating a functionally graded turbine engine component comprising:
- depositing layers of powder onto a base;
- solidifying and fusing each layer with a first directed energy beam to define a component;
- and
- varying a process parameter between deposited layers to define different material properties within the component, further comprising varying the energy level from the first directed energy beam to vary a density of a solidified layer of powder.
A method of fabricating a turbine disk comprising:
- depositing layers of powder onto a base;
- solidifying and fusing each layer with a first directed energy beam to define the turbine disk;
- varying a process parameter between deposited layers to define different material properties within the turbine disk;
- and
- heat treating a solidified layer using a second directed energy beam to induce compressive residual stress into solidified layers of powder.
Dependencies are inferred from the claim text.