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Preparation method of long-life thermal barrier coating

A thermal barrier coating, long-life technology, applied in coating, metal material coating process, solid-state diffusion coating, etc., can solve the problems of high preparation cost and high cost of arc ion plating metal targets, and reduce processing costs. , The effect of high thermal shock resistance and improved service life

Inactive Publication Date: 2018-06-08
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] However, the preparation process of thermal barrier coatings for turbine blades includes arc ion plating coating metal bottom layer, electron beam vapor deposition ceramic surface layer, the preparation cost of this type of turbine blade thermal barrier coating system is relatively high, especially the cost of arc ion plating metal targets higher

Method used

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  • Preparation method of long-life thermal barrier coating
  • Preparation method of long-life thermal barrier coating
  • Preparation method of long-life thermal barrier coating

Examples

Experimental program
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Effect test

Embodiment 1

[0032] Embodiment 1 provides a method for preparing a long-life thermal barrier coating, including the following steps:

[0033] (1) Pretreatment: Before preparing the Al-infiltrated bonding layer, the parts are pretreated, and the pretreatment includes: wet sand blasting and ultrasonic cleaning.

[0034] (2) Preparation of vapor phase infiltration agent: use 3Kg of FeAl powder infiltration agent for every 10 parts, NH 4 Cl catalyst 100g, and baked at 100°C for 1 hour.

[0035] (3) Put the pre-treated blades and the baked infiltration agent into the bonding layer tooling, close the muffle furnace door, use a mechanical pump to evacuate to 1Pa, then pass in argon to 0.1MPa, use argon The air in the furnace was replaced five times, and finally argon was introduced to 0.05MPa. Heat up to 1000°C and keep it warm for 5 hours; during the heat preservation process, when the pressure is greater than 2MPa, deflate to 0.05MPa.

[0036] (4) After the holding time in the furnace is ove...

Embodiment 2

[0043] Embodiment 2 provides a method for preparing a long-life thermal barrier coating, including the following steps:

[0044] (1) Pre-treatment: Before preparing the Al-infiltrated bonding layer, pre-treat the parts. The pre-treatment includes: wet sand blasting and ultrasonic cleaning;

[0045] (2) Preparation of vapor phase infiltration agent: use 5Kg of FeAl powder infiltration agent and 200g of NH4Cl catalyst for every 20 parts; and bake at 150°C for 1 hour,

[0046] (3) Put the pre-treated blades and baked penetrating agent into the bonding layer tooling, close the muffle furnace door; use a mechanical pump to evacuate to 1Pa, then pass in neon gas to 0.2MPa, use neon gas The air in the furnace is replaced six times, and finally neon gas is introduced to 0.05MPa. Heat up to 1020°C and keep it warm for 3 hours; during the heat preservation process, when the pressure is greater than 2MPa, deflate to 0.05MPa.

[0047] (4) After the holding time in the furnace is over, v...

Embodiment 3

[0053] Embodiment 3 provides a method for preparing a long-life thermal barrier coating, including the following steps:

[0054] (1) Pre-treatment: Before preparing the Al-infiltrated bonding layer, pre-treat the parts. The pre-treatment includes: wet sand blasting and ultrasonic cleaning;

[0055] (2) Preparation of vapor phase infiltration agent: use 8Kg of FeAl powder infiltration agent and 200g of NH4Cl catalyst for every 20 parts; and bake at 100°C for 2 hours,

[0056] (3) Put the pre-treated blades and the baked infiltration agent into the bonding layer tooling, close the muffle furnace door; use a mechanical pump to evacuate to 1Pa, then pass in argon to 0.2MPa, use argon The air in the furnace was replaced seven times, and finally argon was introduced to 0.05MPa. Heat up to 1040°C and keep it warm for 2 hours; during the heat preservation process, when the pressure is greater than 2MPa, deflate to 0.05MPa.

[0057] (4) After the holding time in the furnace is over, ...

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Abstract

The invention discloses a preparation method of a long-life thermal barrier coating, belonging to the technical field of thermal barrier coatings for aero-engine turbine blades. A bonding layer of thethermal barrier coating is prepared by using a lower-cost gas-phase infiltration Al method; when being prepared, the bonding layer is in an inert atmosphere, and is subjected to heat preservation andvacuum heat treatment; a ceramic layer of the thermal barrier coating is prepared by using an electron beam vapor deposition method. The gas-phase infiltration Al method is used for replacing an arcion plating method to prepare the bonding layer of the thermal barrier coating, so that the coating processing cost is greatly reduced, and the prepared gas-phase infiltration Al bonding layer has higher Al content; after the ceramic coating is deposited, the thermal shock resistance of the coating is higher, and the service life of the coating is greatly prolonged.

Description

technical field [0001] The invention relates to the technical field of thermal barrier coatings for aeroengine turbine blades, in particular to a preparation method for long-life thermal barrier coatings. Background technique [0002] Because the electron beam physical vapor deposition (EB-PVD) technology has the advantages of easy and precise control of the chemical composition of the coating, the columnar grain structure can be obtained, and the bonding strength between the coating and the substrate is high, it has been widely used in the preparation of various high-temperature protective coatings for turbine blades. Machining significantly improves the high temperature oxidation resistance, corrosion resistance and heat insulation performance of turbine blades, prolonging the working life of the engine. [0003] However, the preparation process of thermal barrier coatings for turbine blades includes arc ion plating coating metal bottom layer, electron beam vapor depositio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C14/30C23C14/02C23C10/08
CPCC23C14/30C23C10/08C23C14/025
Inventor 王玉锋张华常羽彤赵闯古宏博孙惠娴徐杏杏赵志雄
Owner AECC AVIATION POWER CO LTD
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