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Method for manufacturing a thermal-barrier protection and multi-layer coating suitable for forming a thermal barrier

A protective layer, thermal barrier technology, applied in the direction of coating, metal material coating process, blade support elements, etc., can solve the problem of depositing material layers, etc.

Active Publication Date: 2014-11-19
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A +2
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0025] However, these techniques have a number of drawbacks, one of which is that they require the deposition of additional material layers in a rather difficult way

Method used

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  • Method for manufacturing a thermal-barrier protection and multi-layer coating suitable for forming a thermal barrier
  • Method for manufacturing a thermal-barrier protection and multi-layer coating suitable for forming a thermal barrier
  • Method for manufacturing a thermal-barrier protection and multi-layer coating suitable for forming a thermal barrier

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Embodiment Construction

[0070] The surface of a portion of the thermomechanical component shown in FIG. 1 includes a thermal barrier coating 11 deposited on a matrix 12 of a superalloy, such as a nickel and / or cobalt based superalloy. The thermal barrier coating 11 includes a metal sublayer 13 deposited on a substrate 12 and a ceramic layer 14 deposited on the sublayer 13 .

[0071] The adhesion sublayer 13 is a metal sublayer composed of nickel aluminide.

[0072] The ceramic layer 14 consists of yttria zirconia (partially stabilized zirconia) comprising a molar content of yttrium oxide between 4% and 12%. Stabilized zirconia 14 may also in some cases comprise oxides of at least one element selected from the group of rare earths, preferably from the subgroups: Y (yttrium), Dy (dysprosium), Er (erbium), Eu (europium), Gd (gadolinium), Sm (samarium), Yb (ytterbium), or a combination of tantalum (Ta) oxide and at least one rare earth oxide, or a combination of niobium (Nb) oxide and at least one rare ...

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Abstract

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.

Description

technical field [0001] The present invention relates to a method of manufacturing a thermal barrier protection for covering a superalloy metal substrate, to a multilayer coating suitable for forming a thermal barrier on a superalloy metal substrate, and to a process resulting from such a manufacturing method and / or comprising Such coatings for thermomechanical components. Background technique [0002] Especially in the field of aeronautics, research to increase the output of turbine engines, and to reduce fuel consumption, to reduce polluting emissions of gas and unburned compounds has led to a closer approach to the stoichiometry of fuel combustion. This condition is accompanied by an increase in the temperature of the gas flowing from the combustion chamber to the turbine. [0003] Today, the limiting temperature for the use of superalloys is of the order of 1100°C. The temperature of the gas at the exit of the combustor or the gas at the inlet of the turbine can reach 1...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C18/04C23C18/12
CPCF01D5/288C23C18/1254C23C18/1216C23C18/1245Y10T428/12479Y10T428/12549Y02T50/60
Inventor 贾斯汀·曼纽伊弗洛伦斯·昂萨特吉恩-皮埃尔·博尼诺贾斯汀·范尼施赛琳·维阿兹
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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