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US 2019/0211438 A1Published application
Method for producing a thermal barrier system on a metal substrate of a turbo engine part
AssigneeSafran
InventorsNihad BEN SALAH, Jawad BADREDDINE, Aurélian JOULIA
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Abstract
Method for producing a thermal barrier system on a metal substrate (1) of a turbo engine part, such as a high-pressure turbine blade, the thermal barrier system comprising at least one columnar ceramic layer (31, . . . , 3i, . . . , 3n), characterised in that the method comprises a step of compressing at least one of said at least one columnar ceramic layer (31, . . . 3i, . . . , 3n).
Claims15
Method for producing a thermal barrier system on a metal substrate (1) of a turbine engine part, such as a high-pressure turbine blade, the thermal barrier system comprising at least one columnar ceramic layer (3;
- 31, . . . , 3i, . . . , 3n), characterised in that the method comprises a step of compressing at least one of said at least one columnar ceramic layer (3;
- 31, . . . , 3i, . . . , 3n), wherein the compression is capable of reducing the spaces between the columns of the compressed columnar ceramic layer or layers (3;
- 31, . . . , 3i, . . . , 3n).
(canceled)
Dependencies are inferred from the claim text.