Turbine part made of superalloy comprising rhenium and/or ruthenium and associated manufacturing method
The present invention concerns a turbine part comprising a substrate made of nickel-based monocrystalline superalloy, comprising chromium and at least one element chosen among rhenium and ruthenium, the substrate having a γ-γ′ phase, an average mass fraction of rhenium and of ruthenium greater than or equal to 4% and an average mass fraction of chromium less than or equal to 5% and preferably less than or equal to 3%, a sub-layer covering at least a part of a surface of the substrate, characterised in that the sublayer has a γ-γ′ phase and an average atomic fraction of chromium greater than 5%, of aluminium between 10% and 20% and of platinum between 15% and 25%.
1. A process for manufacturing a turbine part comprising a single-crystal nickel-base superalloy substrate and a sublayer,
the single-crystal nickel-base superalloy substrate having a γ-γ′ phase, comprising chromium with an average mass fraction of chromium less than or equal to 5%, and comprising at least one element selected from rhenium and ruthenium, with an average mass fraction of rhenium greater than or equal to 4% when there is no ruthenium, with an average mass fraction of ruthenium greater than or equal to 4% when there is no rhenium and with an average mass fraction of the total of rhenium and ruthenium greater than or equal to 4% when there is rhenium and ruthenium
the sublayer covering at least part of a surface of the substrate,
the sublayer having a γ-γ′ phase and an average atomic fraction:
of chromium comprised between 5% and 10%,
of aluminum comprised between 10% and 20%,
of platinum comprised between 15% and 25%,
wherein the process comprises at least the steps of:
depositing an enrichment layer on the substrate, the enrichment layer having at least an average atomic fraction of platinum greater than 90% and an average atomic fraction of chromium comprised between 3% and 10%,
heat treating the assembly formed by the substrate and the enrichment layer so that the enrichment layer diffuses at least partially into the substrate.
2. The process as claimed in claim 1 , wherein, during step a) of depositing an enrichment layer, at least one chromium layer and one platinum layer are deposited separately, the chromium layer or layers having a total thickness comprised between 200 nm and 2 μm and the platinum layer or layers having a total thickness comprised between 3 μm and 10 μm.
3. The process as claimed in claim 1 , wherein, during step a) of depositing an enrichment layer, chromium and platinum are deposited simultaneously.
4. The process as claimed in claim 1 , wherein the assembly formed by the substrate and the enrichment layer is heat treated at a temperature above 1000° C. for more than one hour.
5. The process as claimed in claim 1 , wherein the deposition of the enrichment layer is carried out by a method selected from physical vapor deposition, thermal spraying, electron beam evaporation, pulsed laser ablation and cathode sputtering.
6. The process as claimed in claim 1 , wherein the single-crystal nickel-base superalloy substrate has an average mass fraction of chromium less than or equal to 3%.
7. The process as claimed in claim 1 , wherein the assembly formed by the substrate and the enrichment layer is heat treated at a temperature above 1000° C. for more than 2 hours.