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

Claim 7:
8. A method for manufacturing a turbine engine blade, the turbine engine blade including a bathtub tip portion having an active-surface wall, a passive-surface wall spaced from the active-surface wall, and a closing wall grouping together the active-surface wall and passive-surface wall, the active-surface wall and the passive-surface wall each extending continuously beyond the closing wall to respective top edges, the bathtub tip portion having a bathtub tip shape, the method comprising:
a moulding step implementing a removable core, the removeable core defining after removal a full extent of the bathtub tip portion, including the respective top edges of the active- and passive-surface walls,
a step of adding metal to the closing wall at the bottom of the bathtub tip portion with an additive manufacturing method adding metal, by depositing metal powder on the closing wall to form an inner partition supported by the closing wall, the inner partition having an extremity joining the top edge of the active-surface wall and another extremity joining the top edge of the passive-surface 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.