METHOD FOR MANUFACTURING A BLADE

Abstract

The invention relates to a method for manufacturing a turbine blade for an aircraft turbomachine, characterized in that the method comprises the following steps: (a) providing a foot (13) comprising a composite material, (c) forming a sleeve (14) around the foot (13), the sleeve (14) extending about an axis of elongation, step (c) comprising the following sequential substeps: (c1) depositing a first layer (16) around the foot (13) along an axis of revolution centered on the foot (13), by dynamic cold gas spraying, and (c2) depositing a second metallic layer (18) around the first layer (16) along the axis of revolution, by deposition under concentrated energy. (Short figure: Figure 8)

Claims

Demands

1. A method for manufacturing a blade (11) for an aircraft turbomachine (1), characterized in that the method comprises the following steps: (a) providing a foot (13) comprising a composite material, (c) forming a sleeve (14) around the foot (13), the sleeve (14) extending around an axis of elongation (X), step (c) comprising the following chronological substeps: (c1) depositing a first layer (16) around the foot (13) along an axis of revolution (X) centered on the foot (13), by dynamic cold gas projection, and (c2) depositing a second metallic layer (18) around the first layer (16) along the axis of revolution (X), by deposition under concentrated energy.

2. Method according to the preceding claim, characterized in that step (cl) is carried out by a mobile or fixed cold gas dynamic projection device, the foot (13) being mobile or fixed.

3. A method according to any one of the preceding claims, characterized in that step (c2) is carried out by a mobile or fixed concentrated energy deposition device, the foot (13) being mobile or fixed.

4. A method according to any one of the preceding claims, characterized in that the first layer (16) comprises a metallic material, preferably a titanium alloy.

5. A method according to any one of the preceding claims, characterized in that the second layer (18) comprises a titanium alloy.

6. A method according to any one of the preceding claims, characterized in that the first layer (16) has a first thickness (el) between 5 pm and 200 pm.

7. Method according to the preceding claim, characterized in that the second layer (18) has a second thickness (e2) greater than the first thickness (el) of the first layer.

8. A method according to any one of the preceding claims, characterized in that it comprises, between steps (a) and (c), a step (a') of checking the foot (13), for example by tomography.

9. A method according to any one of the preceding claims, characterized in that it comprises, after step (c), a step (d) of machining the sleeve (14).

10. A method according to any one of the preceding claims, characterized in that it comprises after step (a), a step (b) of inserting an insert (15) into the foot (13).

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