公开(公告)号：US12012869B2

公开(公告)日：2024-06-18

申请号：US16958422

申请日：2018-12-26

Applicant: SAFRAN

Inventor： Luc Bianchi ,  Aurélien Joulia ,  André Hubert Louis Malie ,  Benjamin Dominique Roger Joseph Bernard

IPC: C04B41/89 ,  C04B41/00 ,  C04B41/50 ,  C04B41/52 ,  F01D5/28 ,  F01D25/00

CPC classification number: F01D5/288 ,  C04B41/009 ,  C04B41/5024 ,  C04B41/5042 ,  C04B41/5072 ,  C04B41/522 ,  C04B41/89 ,  F01D25/00 ,  F05D2220/30 ,  F05D2230/31 ,  F05D2230/90

Abstract: The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.

公开(公告)号：US11976570B2

公开(公告)日：2024-05-07

申请号：US17414208

申请日：2019-12-20

Applicant: SAFRAN

Inventor： Aurélien Joulia ,  Benjamin Dominique Roger Joseph Bernard ,  Luc Patrice Bianchi

IPC: F01D5/28 ,  C04B41/50

CPC classification number: F01D5/288 ,  C04B41/5035 ,  C04B41/5042 ,  C04B41/5045 ,  F01D5/284 ,  F05D2300/211 ,  F05D2300/2112 ,  F05D2300/611

Abstract: The invention relates to an aeronautical part, such as, for example, a turbine blade or a distributor vane, which is used in aeronautics, comprising at least one reactive layer adapted to react with at least one CMAS compound, the reactive layer at least partially covering the environmental barrier, characterized in that the material of the reactive layer comprises at least one oxide of the formula A′4-xA″xB′2-yB″yO11-δ, A′ being selected from a rare earth, yttrium and scandium, A″ being selected from a rare earth, yttrium, scandium and aluminum, B′ being selected from tantalum and niobium, B″ being selected from tantalum, niobium, titanium, zirconium, hafnium, aluminum and cesium, wherein x and y are real numbers between 0 and 2 and 6 is a real number between −1 and 2 and preferably between −1 and 1.

公开(公告)号：US11473432B2

公开(公告)日：2022-10-18

申请号：US16621535

申请日：2018-06-12

Applicant: SAFRAN

Inventor： Luc Bianchi ,  Aurélien Joulia ,  Benjamin Dominique Roger Joseph Bernard

IPC: F01D5/28 ,  C23C4/04 ,  C23C4/11 ,  C23C4/129 ,  C23C4/134 ,  C23C4/10

Abstract: A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.