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US 11,060,178 B2Granted
Method for producing a thermal barrier system on a metal substrate of a turbo engine part
AssigneeSafran
InventorsNihad Ben Salah, Jawad Badreddine, Aurélian Joulia
Life of this patent
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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).
Claims19
A method for producing a thermal barrier system on a metal substrate of a turbine engine part,
- said thermal barrier system comprising a stack of a plurality of columnar ceramic layers which have an upper ceramic layer and at least one intermediate ceramic layer arranged under said upper ceramic layer,
- said upper ceramic layer forming a top of said stack of plurality of columnar ceramic layers,
- said upper ceramic layer comprising a lower surface which is in contact with said at least one intermediate ceramic layer and an upper surface which is not in contact with any layer,
- said at least one intermediate ceramic layer being arranged between said upper ceramic layer and said metal substrate,
- the method comprising the steps of:
- successively depositing said plurality of columnar ceramic layers on said metal substrate,
- stacking said at least one intermediate ceramic layer on said metal substrate,
- compressing said at least one intermediate ceramic layer to tighten spaces between columns of said at least one intermediate ceramic layer, and
- stacking said upper ceramic layer on said at least one intermediate ceramic layer.
6 more elements
Dependencies are inferred from the claim text.