Process for the vapor phase aluminization of a turbomachine metal part and donor liner and turbomachine vane comprising such a liner
View Patent ↗An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.
1. A hollow turbomachine vane including a liner for distributing cooling air,
the liner being cylindrical,
the liner including a first end which is welded or brazed to a coolant supplying opening of the vane and a second end which is introduced into and not welded to a housing which communicates with an outlet of the vane, and
a surface of the liner being coated, at least partially, with a layer of at least 15 weight percent of aluminum,
wherein a thickness of the layer of aluminum is determined so as to have a sufficient amount of aluminum to react with a halogen to form a vapor-phase halide during an aluminization operation of an internal surface of the vane, and
wherein the internal surface of the vane is free of a coating comprising aluminum.
2. The vane as claimed in claim 1 , wherein the aluminum layer is between 10 and 150 μm.
3. The vane as claimed in claim 2 , wherein the aluminum layer is between 20 and 90 μm.
4. A turbomachine nozzle comprising the hollow vane of claim 1 .
5. The vane as claimed in claim 1 , wherein the liner is perforated with at least one perforation.
6. The vane as claimed in claim 5 , wherein a space is provided between the liner and an inner wall of the vane such that cooling air coming from the coolant supplying opening passes through at least one perforation of the liner to form air jets.
7. The vane as claimed in claim 1 , wherein the liner comprises a cobalt-based alloy.
8. The vane as claimed in claim 1 , wherein the layer which coats the liner further comprises at least one of Cr, Hf, Y, Zr, Si, Ti, Ta, Pt, Pd, and Ir.
9. The vane as claimed in claim 1 , wherein a zone of the surface of the liner that is brazed is uncoated.