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Preparation technology of thermal barrier coating of blade of aviation engine

A technology of aero-engine and thermal barrier coating, applied in the field of laser applications, to achieve the effect of improving bonding strength and reducing damage

Active Publication Date: 2018-07-31
JIANGSU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, as far as the working conditions of the turbine blade are concerned, even with advanced film cooling technology, the temperature of the gas reaching the blade surface is still higher than the temperature limit of the blade alloy

Method used

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  • Preparation technology of thermal barrier coating of blade of aviation engine
  • Preparation technology of thermal barrier coating of blade of aviation engine
  • Preparation technology of thermal barrier coating of blade of aviation engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0046] (1) CoCrAlY coating was prepared by plasma spraying on 5 samples of nickel-based superalloy GH4586 as the bonding layer of thermal barrier coating. The preparation process parameters are shown in Table 1. Thickness 130μm.

[0047] (2) Spray 8YSZ coating on the bonding layer, the specific process parameters are shown in Table 2. The thickness is 52 μm.

[0048] (3) The surface of the ceramic layer is pre-treated by laser etching using a Nd:YAG laser. The specific process parameters are as follows: the working wavelength is 1064nm, the pulse width is 10ps, the pulse energy is 60J, the focal length of the focusing lens is 250mm, and the scanning speed of the galvanometer is 15mm / s. The distributed isosceles trapezoidal groove structure has the following dimensions: the length of the upper base is 101.6 μm, the length of the lower base is 50.5 μm, and the height is 50.8 μm. The pitch of the isosceles trapezoidal grooves is about 150.3 μm.

[0049] (4) Plasma spraying was...

Embodiment 2

[0055] (1) CoCrAlY coating was prepared by plasma spraying on 5 samples of nickel-based superalloy GH4586 as the bonding layer of thermal barrier coating. The preparation process parameters are shown in Table 1. The thickness is 131 μm.

[0056] (2) Spray 8YSZ coating on the bonding layer, the specific process parameters are shown in Table 2. The thickness is 52 μm.

[0057] (3) The surface of the ceramic layer is pre-treated by laser etching using a Nd:YAG laser. The specific process parameters are as follows: the working wavelength is 1060nm, the pulse width is 10ps, the pulse energy is 70J, the focal length of the focusing lens is 250mm, and the scanning speed of the galvanometer is 20mm / s. The isosceles trapezoidal groove structure distributed in parallel, its size is: the length of the upper base is 100.3 μm, the length of the lower base is 50.7 μm, and the height is 50.6 μm. The pitch of the isosceles trapezoidal grooves is about 150.5 μm.

[0058] (4) Plasma spraying...

Embodiment 3

[0064] (1) CoCrAlY coating was prepared by plasma spraying on 5 samples of nickel-based superalloy GH4586 as the bonding layer of thermal barrier coating. The preparation process parameters are shown in Table 1. The thickness is 138 μm.

[0065] (2) Spray 8YSZ coating on the bonding layer, the specific process parameters are shown in Table 2. The thickness is 51 μm.

[0066] (3) The surface of the ceramic layer is pre-treated by laser etching using a Nd:YAG laser. The specific process parameters are as follows: the working wavelength is 532nm, the pulse width is 10ps, the pulse energy is 80J, the focal length of the focusing lens is 250mm, and the scanning speed of the galvanometer is 30mm / s. The isosceles trapezoidal groove structure distributed in parallel, its size is: the length of the upper base is 100.2 μm, the length of the lower base is 50.3 μm, and the height is 50.4 μm. The pitch of the isosceles trapezoidal grooves is about 105.5 μm.

[0067] (4) Plasma spraying ...

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Abstract

The invention relates to the technical field of laser application, and further relates to a preparation technology of a thermal barrier coating of a blade of an aviation engine. Picosecond laser is utilized for carrying out etching process treatment during a preparation process of a bonding layer-bonding layer interface of the thermal barrier coating, and an interface tenon-shaped staggering structure is obtained, so that the bonding strength between a plasma spraying ceramic layer and a bonding layer is improved. During a high-temperature cyclic oxidation process, a thermal stress distribution state of the coating interface is effectively adjusted, a concentrated stress mode of the coating is changed, a growth model of constant-speed and plane propulsion of thermally grown oxide (TGO) isbroken, and the damage of a thermal stress and the growth way of the TGO on a binding force of the bonding layer and the ceramic layer is reduced. Through a thermal shock property experiment, the service life of the thermal barrier coating impacted by the bonding layer is greatly prolonged. A thermal barrier coating interface structure adjusting method provided by the invention is simple in process, easy to operate and convenient to implement.

Description

technical field [0001] The invention relates to the technical field of laser application, and also relates to a preparation process of an aeroengine blade thermal barrier coating. Background technique [0002] The high-pressure turbine blade is the core component with the most demanding temperature and load bearing in the engine, and it is also a short board that restricts the development of the engine. At present, superalloys are the main structural materials used in high-pressure turbine blades. Among them, single crystal alloys have the highest temperature-bearing capacity, and the highest temperature they can withstand is about 1150 ° C, which is close to the temperature-bearing limit of superalloys. However, as far as the working conditions of the turbine blades are concerned, even with advanced film cooling technology, the temperature of the gas reaching the blade surface is still higher than the temperature tolerance limit of the blade alloy. In response to this prob...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/18C23C4/073C23C4/11
CPCC23C4/073C23C4/11C23C4/134C23C4/18
Inventor 花银群李志宝叶云霞曹将栋帅文文陈瑞芳薛青
Owner JIANGSU UNIV
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