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1.发明授权公开(公告)号：US09121295B2
公开(公告)日：2015-09-01
申请号：US13634420
申请日：2011-03-11
CPC分类号： F01D5/288 , C23C18/1216 , C23C18/1245 , C23C18/1254 , Y10T428/12479 , Y10T428/12549
摘要： The invention relates to a method for manufacturing a thermal barrier protection covering a superalloy metal substrate and comprising at least one metal sublayer (13) and a ceramic layer (14) based on zirconia stabilized with yttrium having a column structure defining pores.The following steps are applied: impregnation of a portion of the pores of the ceramic layer (14) with a sol based on zirconia is achieved via a sol-gel route and this in order to form an anchoring sublayer (22), on said ceramic layer topped with said anchoring sub-layer (22), a continuous protective layer (20) based on oxide, is formed via a sol-gel route, and a heat treatment is carried out, whereby an outer protection layer is formed against the attack of the thermal barrier (11) by CMASes. Application to the protection of aeronautical protection parts.
摘要翻译： 本发明涉及一种用于制造覆盖超合金金属基底的热障保护的方法，该方法包括至少一个金属子层（13）和陶瓷层（14），所述金属子层（13）和陶瓷层（14）基于用具有限定孔的柱结构的用钇稳定的氧化锆。 应用以下步骤：通过溶胶 - 凝胶途径实现用基于氧化锆的溶胶浸渍陶瓷层（14）的一部分孔隙，以便在所述陶瓷上形成锚定子层（22） 通过溶胶 - 凝胶途径形成基于氧化物的连续保护层（20），并且进行热处理，从而形成抵抗攻击的外部保护层 的热障（11）。 适用于航空保护部件的保护。
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2.发明申请公开(公告)号：US20130130052A1
公开(公告)日：2013-05-23
申请号：US13634420
申请日：2011-03-11
IPC分类号： F01D5/28
CPC分类号： F01D5/288 , C23C18/1216 , C23C18/1245 , C23C18/1254 , Y10T428/12479 , Y10T428/12549
摘要： The invention relates to a method for manufacturing a thermal barrier protection covering a superalloy metal substrate and comprising at least one metal sublayer (13) and a ceramic layer (14) based on zirconia stabilized with yttrium having a column structure defining pores.The following steps are applied: impregnation of a portion of the pores of the ceramic layer (14) with a sol based on zirconia is achieved via a sol-gel route and this in order to form an anchoring sublayer (22), on said ceramic layer topped with said anchoring sub-layer (22), a continuous protective layer (20) based on oxide, is formed via a sol-gel route, and a heat treatment is carried out, whereby an outer protection layer is formed against the attack of the thermal barrier (11) by CMASes. Application to the protection of aeronautical protection parts.
摘要翻译： 本发明涉及一种用于制造覆盖超合金金属基底的热障保护的方法，该方法包括至少一个金属子层（13）和陶瓷层（14），所述金属子层（13）和陶瓷层（14）基于用具有限定孔的柱结构的用钇稳定的氧化锆。 应用以下步骤：通过溶胶 - 凝胶途径实现用基于氧化锆的溶胶浸渍陶瓷层（14）的一部分孔隙，以便在所述陶瓷上形成锚定子层（22） 通过溶胶 - 凝胶途径形成基于氧化物的连续保护层（20），并且进行热处理，从而形成抵抗攻击的外部保护层 的热障（11）。 适用于航空保护部件的保护。
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