Patent ID: 11925986
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Materials, metallurgy (Chemistry)
Classification: CPC B  F  Y | IPC B  F

Claim 12:
13. A method for manufacturing a turbine engine blade, the turbine engine blade having a bathtub tip portion that includes an active-surface wall, a passive-surface wall, and a closing wall grouping together the active-surface wall and passive-surface wall, the active- and passive-surface walls each extending beyond the closing wall to respective top edges of the active- and the passive-surface walls, the bathtub tip portion having a bathtub tip shape, the method comprising:
a moulding step that forms the closing wall by moulding;
an additive manufacturing step of adding metal to the closing wall by depositing metal powder on the closing wall to form an inner partition supported by the closing wall; and
a machining step, for machining the deposited metal powder to carryout shape finishing of the inner partition, the machining step occurring after the step of adding metal.