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High-performance thermal barrier coating for heavy duty gas turbine blade, and multi-process combination preparation method thereof

A technology of gas turbine blades and thermal barrier coatings, which is applied in the direction of metal material coating technology, coating, fusion spraying, etc., can solve the problems of affecting the service life of blades and low bonding strength, so as to improve the service life and increase the contact area , Improve the effect of surface quality

Active Publication Date: 2020-08-28
JIANGSU UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to invent a high-performance thermal barrier coating for heavy-duty gas turbine blades and provide corresponding multi- The process combination preparation method, that is: using laser cladding (LC) technology to prepare MCrAlY bonding layer + laser shock composite strengthening technology to regulate the structure of the bonding layer + APS technology to prepare YSZ ceramic layer, the TBCs system has excellent interface bonding strength, High high temperature oxidation resistance and thermal shock performance, which solves the needs of gas turbine thermal barrier coatings for high heat insulation, oxidation resistance, long life and large-area controllable preparation

Method used

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  • High-performance thermal barrier coating for heavy duty gas turbine blade, and multi-process combination preparation method thereof
  • High-performance thermal barrier coating for heavy duty gas turbine blade, and multi-process combination preparation method thereof
  • High-performance thermal barrier coating for heavy duty gas turbine blade, and multi-process combination preparation method thereof

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Experimental program
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Effect test

Embodiment 1

[0035] The thermal barrier coating is prepared by using the superalloy base material for gas turbine blades as the carrier. The process flow is: sample inspection→grinding and polishing→ultrasonic cleaning→laser cladding technology to prepare MCrAlY bonding layer→machining→grinding and polishing→ultrasonic Cleaning→Large area laser shock strengthening treatment→Grinding and polishing→Selective laser shock micro-modeling treatment→Sandblasting→Preparation of YSZ ceramic layer by atmospheric plasma spraying→Inspection.

[0036] The coating preparation steps are:

[0037] (1) Grinding and polishing the blade base material, followed by ultrasonic cleaning;

[0038] (2) The MCrAlY (M=Ni) bonding layer is prepared by laser cladding technology. The coating powder is about 200 meshes. The laser cladding process parameters are selected as laser power 1.8Kw, scanning speed 600mm / min, and powder feeding rate 1.2 r / min, the spot diameter is 3mm, the overlap rate is 50%, and the thickness of th...

Embodiment 2

[0047] The preparation of TBCs was carried out according to the steps described in Example 1, the difference is:

[0048] The coating preparation steps are:

[0049] (1) Grinding and polishing the base material, followed by ultrasonic cleaning;

[0050] (2) The MCrAlY (M=Ni) bonding layer is prepared by laser cladding technology. The coating powder is about 200 meshes. The laser cladding process parameters are selected as laser power 2.0Kw, scanning speed 800 mm / min, and powder feeding rate 1.5r / min, the spot diameter is 3mm, the overlap rate is 50%, and the thickness of the cladding layer is 1000μm;

[0051] (3) Machine processing to remove the oxide scale on the surface of the cladding layer, and the cladding layer is polished, polished and ultrasonically cleaned to obtain the best surface condition to be impacted;

[0052] (4) Using nano lasers to perform large-area laser shock strengthening treatment on the surface of the MCrAlY cladding layer, choose aluminum foil as the absorpti...

Embodiment 3

[0059] The thermal barrier coating is prepared by using the superalloy base material for gas turbine blades as the carrier. The process flow is: sample inspection→grinding and polishing→ultrasonic cleaning→laser cladding technology to prepare MCrAlY bonding layer→machining→grinding and polishing→ultrasonic Cleaning→Large area laser shock strengthening treatment→Grinding and polishing→Selective laser shock micro-modeling treatment→Sandblasting→Preparation of YSZ ceramic layer by atmospheric plasma spraying→Inspection.

[0060] The coating preparation steps are:

[0061] (1) Grinding and polishing the blade base material, followed by ultrasonic cleaning;

[0062] (2) Using laser cladding technology to prepare MCrAlY (M=Ni) bonding layer, the coating powder is about 300 meshes, and the laser cladding process parameters are selected as laser power 2.2Kw, scanning speed 800mm / min, and powder feeding rate 1.4r / min, the spot diameter is 4mm, the overlap rate is 30%, and the thickness of t...

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Abstract

The invention provides a high-performance thermal barrier coating for a heavy duty gas turbine blade, and a multi-process combination preparation method thereof, and belongs to the technical field ofgas turbine blade thermal barrier coatings. The preparation method comprises the steps of preparing an MCrAlY bonding layer with a laser cladding technology, and regulating an MCrAlY cladding layer structure and stress state with a laser shock strengthening technology largely; machining a micro-pit structure in the surface of a strengthening layer with a laser shock micro-modeling technology selectively, and preparing a YSZ ceramic layer with an atmospheric plasma spraying technology; and controlling the corresponding parameters to obtain the thermal barrier coating. The thermal barrier coating provided by the invention is higher interface bonding strength, high temperature oxidation resistance and thermal shock resistance; and the requirements of the thermal barrier coating of a gas turbine for high thermal insulation, oxidation resistance, long life and large-area controllable preparation are met; and the preparation method has broad market prospects.

Description

Technical field [0001] The invention relates to a surface treatment technology, in particular to a gas turbine coating protection technology, in particular to a heavy-duty gas turbine turbine blade high heat insulation, oxidation resistance, long-life thermal barrier coating and a multi-process combined preparation method thereof . Background technique [0002] At present, the gas temperature of the most advanced heavy-duty gas turbine in the world has reached 1600 o C, the future o C and above development. This extreme high temperature environment has exceeded the limit temperature of the turbine blades. The use of advanced thermal barrier coatings (TBCs) technology is the most economical and effective way for gas turbines to achieve high efficiency, low emissions and long life. . The commonly used TBCs are mainly composed of YSZ (Y 2 O 3 Partially stable ZrO 2 ) Ceramic surface layer and MCrAlY (M=Ni, Co, Ni+Co) metal bonding layer that resists oxidation and corrosion and reli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/10C23C4/134C23C4/11
CPCC23C24/106C23C4/134C23C4/11
Inventor 蔡杰姚逸铭张从林关庆丰鲁金忠孟宪凯李玉新
Owner JIANGSU UNIV
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