CPC F01D 5/288 (2013.01) [C22C 19/057 (2013.01); C23C 10/28 (2013.01); C23C 28/3215 (2013.01); C23C 28/3455 (2013.01); F05D 2230/31 (2013.01); F05D 2230/40 (2013.01); F05D 2300/132 (2013.01); F05D 2300/143 (2013.01); F05D 2300/175 (2013.01); F05D 2300/607 (2013.01)] | 7 Claims |
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.
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