Method for manufacturing a blade for a turbomachine
AssigneesSafran, Safran Aero Boosters SA
InventorsYann Jean-Pierre Lefaux, Pierre Jean Sallot
Life of this patent
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Abstract
A method for manufacturing a blade for a turbine engine, including a root connected to a vane extending in a longitudinal direction, includes providing an assembly having a first part intended to form a root of the blade and a projecting second part projecting in the longitudinal direction from the first part; providing a mold comprising a first impression and a second impression delimiting together a cavity, said cavity comprising a first space and a second space; arranging the first part in the first space of the cavity and the second part in the second space of the cavity; and forming a third part by injecting an aluminium-based alloy in the cavity.
Claims7
A method for manufacturing a blade (2) for a turbine engine, including a root (6) connected to a vane (4) extending in a longitudinal direction, the method comprising the steps:
- providing an assembly (10) comprising:
- a first part (12) intended to form the root (6) of the blade (2), this first part (12) being produced from a titanium-based alloy,
- a projecting second part (14) extending in the longitudinal direction from the first part (12);
- providing a mould comprising a first impression (50) and a second impression (52) delimiting together a cavity (58) in which the blade is intended to be formed, said cavity (58) comprising a first space (64) intended to form the vane and a second space (66) intended to receive the first part;
- arranging the second part in the first space (64) of the cavity (58) and the first part in the second space (66) of the cavity (58);
- injecting an aluminum-based alloy into the cavity, this aluminum-based alloy forming a third part (16) in which the second part (14) is embedded, whereby the second part comprises a general U shape including a first arm (18) and a second arm (20) connected by a top part (22), wherein the first arm (18) and/or the second arm (20) include protrusions (26).
A method for manufacturing a blade (2) for a turbine engine, including a root (6) connected to a vane (4) extending in a longitudinal direction, the method comprising the steps:
- providing an assembly (10) comprising:
- a first part (12) intended to form the root (6) of the blade (2), this first part (12) being produced from a titanium-based alloy,
- a projecting second part (14) extending in the longitudinal direction from the first part (12);
- providing a mould comprising a first impression (50) and a second impression (52) delimiting together a cavity (58) in which the blade is intended to be formed, said cavity (58) comprising a first space (64) intended to form the vane and a second space (66) intended to receive the first part;
- arranging the second part in the first space (64) of the cavity (58) and the first part in the second space (66) of the cavity (58);
- injecting an aluminum-based alloy into the cavity, this aluminum-based alloy forming a third part (16) in which the second part (14) is embedded;
- wherein said second part (14) includes at least one internal air-circulation circuit (28) able to receive hot air coming from outside the blade (2).
Dependencies are inferred from the claim text.