Method for manufacturing a blade for a turbomachine

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.

Claims

1. 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).

2. The method for manufacturing a blade according to claim 1, wherein the assembly (10) is produced by additive manufacturing.

3. The method for manufacturing a blade according to claim 1, wherein the protrusions (26) include protrusions extending transversely towards the inside (26a) of the general U shape and/or protrusions extending transversely towards the outside (26b) of the general U shape.

4. 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).

5. The method for manufacturing a blade according to claim 4, wherein the at least one internal air-circulation circuit (28) comprises air outlets (42) emerging on an external surface of the third part (16).

6. The method for manufacturing a blade according to claim 4, wherein the second part comprises a general U shape including a first arm (18) and a second arm (20) connected by a top part (22).

7. The method for manufacturing a blade according to claim 6, wherein the at least one internal air-circulation circuit (28) comprises air outlets (42) emerging on an external surface of the third part (16).

Description

BRIEF DESCRIPTION OF THE FIGURES

(1) FIG. 1 shows a schematic representation of a turbine-engine blade;

(2) FIG. 2 shows: in FIG. 2A a schematic representation of a first embodiment of an assembly comprising a first part and a second part according to the invention; in FIG. 2B a schematic representation of a first embodiment of the turbine-engine blade seen from the front according to the invention; in FIG. 2C a schematic representation of the first embodiment of the turbine-engine blade seen from the side according to the invention;

(3) FIG. 3 shows a schematic representation of a second embodiment of a turbine-engine blade including an air-circulation circuit according to the invention;

(4) FIG. 4 shows a schematic representation of a third embodiment of a turbine-engine blade including an air-circulation circuit according to the invention;

(5) FIG. 5 shows a schematic representation of a mould according to the invention;

DETAILED DESCRIPTION OF THE INVENTION

(6) The present document relates to a blade 2 comprising a root 6 made from a titanium-based alloy compatible with the materials used for a disc (or collar) carrying said roots 6 of the blade 2.

(7) This compatibility makes it possible to envisage a direct assembly between the blade 2 extending longitudinally and the disc (or collar) by friction welding for example. Said blade 2 furthermore includes a vane 4 comprising an aluminium alloy.

(8) FIG. 2 illustrates a schematic representation of a first embodiment of a turbine-engine blade 2 according to the present document. More precisely FIG. 2A illustrates a schematic representation of an assembly 10 comprising a first part 12 and a second part 14. FIG. 2B is a schematic representation of a turbine-engine blade 2 seen from the front and FIG. 2C is a schematic representation of a turbine-engine blade 2 seen from the side.

(9) As illustrated in FIG. 2, the second part 14 comprises a general U shape adapted to extend projecting from the first part 12 in the longitudinal direction over a longitudinal dimension of between 20 and 90% of the longitudinal dimension of the blade. This second part 14 is intended to form, with a third part 16 the vane of the blade. This second part 14 includes a first arm 18 and a second arm 20 that are connected to each other by a top part 22. The first arm 18 and second arm 20 each comprise an end 24a, 24b on a side opposite to the top part 22. These ends 24a, 24b of the first arm 18 and of the second arm 20 are each connected to the first part 12. One or other or both of the first arm 18 and second arm 20 comprise protrusions 26. These protrusions 26 comprise protrusions extending transversely to the inside 26a of the general U shape and/or protrusions extending transversely towards the outside 26b of the general U shape. These protrusions 26 form attachment zones comprising a surface state such that attachment to the third part 16 is optimised.

(10) The first part 12 is intended to form the root 6 of the blade 2. The first part 12 may have a shape initially distinct from the final shape of the root 6 of the blade 2. This first part 12, which may form a preform of the root, can thus be machined in order to match the final shape of the root 6 of the blade 2 required.

(11) According to a second embodiment illustrated in FIG. 3, the blade 2 includes a first part 12, a second part 14 and a third part 16 in a similar manner to the first embodiment. In this embodiment, the second part 14 includes an internal air-circulation circuit 28. This internal air-circulation circuit 28 includes a first section 30 having an end 32 emerging outside the first part 12, on the opposite side to the vane 4. This internal circulation circuit 28 furthermore comprises a second section 34 passing inside the second part 14 having a general U shape and a third section 36 connected continuously to the second section 34 and emerging outside the first part on the opposite side to the vane.

(12) According to a third particular embodiment illustrated in FIG. 4, the blade 2 includes a first part 12, a second part 14 and a third part 16 in a similar manner to the first embodiment. In this third embodiment, an internal air-circulation circuit 28 begins in the first arm 18 at the end opposite to the top part. This end opposite to the top part 22 includes a first zone 38 adjacent to the first part 12 and a second zone 40 emerging outside the blade 2. This second zone 40 can comprise a single zone emerging outside the blade or a plurality of zones emerging outside the blade over a dimension of between 0 and 80% of a longitudinal dimension of the third part. The second arm 20 of the second part 14 is free, i.e. not connected to the first part 12, and comprises air outlets 42 emerging on an external surface of the third part 16. These air outlets 42 may, for example, be three in number but this number of air outlets is not limitative and there may be a single air outlet or a plurality.

(13) As illustrated in FIG. 5, a mould 44 is used to manufacture such a blade 2. Said blade 2 to be manufactured ultimately matches the geometry of the mould 44. The mould 44 comprises at least a first shell 46 and a second shell 48 which, arranged one against the other, form said mould 44. The first shell 46 includes a first internal face forming a first impression 50. The second shell 48 includes a second internal face forming a second impression 52. When the first shell 46 and the second shell 48 are assembled one against the other, the first impression 50 and the second impression 52 form together a cavity 58 in which the blade is intended to be formed.

(14) The first impression 50 and the second impression 52 each comprise a first zone 60a, 60b and a second zone 62a, 62b. The first zone 60a of the first impression 50 delimits, with a first zone 60b of the second impression 52, a first space 64 of the cavity 58, which is intended to form the vane. The second zone 62a of the first impression 50 delimits, with the second zone 62b of the second impression 52, a second space 66 of the cavity 58, which is intended to receive the first part 12 of the blade 2. The first space 64 of the cavity 58 and the second space 66 of the cavity 58 form together the internal cavity 58 of the mould 44 intended to receive the second part 14 of the blade 2.

(15) The first shell 46 includes a first internal channel 54, a first end of which emerges at the first part 64 of the cavity 58 and a second end of which emerges outside said mould 44. The second shell 48 includes a second internal channel 56, a first end of which emerges at the second part 66 of the cavity 58 and a second end of which emerges outside said mould 44.

(16) The first space 64 of the cavity 58 delimits a zone into which a liquid metal intended to form the third part of the blade is injected. The second space 66 of the cavity 58 is furthermore able to receive in particular the root of the blade preferably manufactured by additive manufacturing.

(17) According to the present document, the first part 12 is arranged in the second space 66 of the cavity 58 and the second part 14 is arranged in the first space 64 of the cavity 58. The aluminium-based alloy is injected so as to form the third part 16 and to embed the second part 14, the second part then being surrounded by the third part. The second 14 and the third part 16 thus form the vane 4 of the blade 2.

(18) It will be understood that the second part 14 ensures attachment of the third part 16 on the second part 14, the latter therefore forming a means of attachment between the root and the third part 16 intended to form the part of the aluminium-alloy vane 2. This is because the shape of the second part 14 and in particular the protrusions produce a large specific surface area providing effective anchoring of the second part 14 with the third part 16. The shape of the second part provides radial mechanical holding and the surface state optimises attachment in a transverse direction by increasing the specific surface area. This surface state furthermore compensates for shrinkages related to a solidification of the third part around the U.

(19) Through its shape, the second part 14 furthermore stiffens the vane when the vane is not sufficiently stiff. This second part 14 therefore forms, through its arrangement and constitution, a means for adjusting the stiffness of the vane.

(20) The internal air-circulation circuit 28 of the second part can heat the vane and thus avoids the accretion of ice by circulation of air in the internal structure of the vane. This internal air-circulation circuit 28 also modifies the aerodynamics of the vane 4 and takes off a limit layer circulating in the vicinity of the external surface of the third part forming a trailing edge.

(21) The first part 12 is advantageously made from a titanium-based alloy having a melting point of between 1600 and 1700 C. and the second is made from an aluminium-based alloy having a melting point of between 500 and 600 C. This difference between the melting points of aluminium and titanium limits the interactions between the third part 16 on the one hand and the first part 12 and the second part 14 on the other hand and thus limits the formation of fragile phases.

(22) The first part 12 and the second part can be obtained by means of an additive manufacturing method. In this way, the second part 14 can have any and shape adapted to the attachment of the third part 16 on the second part 14.