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Composite coating for gas turbine blade

A technology for gas turbine blades and composite coatings, applied in coatings, metal material coating processes, superimposed layer plating, etc., can solve problems such as damage, affecting the stability of nanocrystalline layer structures, and lack of aluminum elements, and achieve improved Stability, avoid premature peeling failure, prevent falling off effect

Active Publication Date: 2018-04-03
ELECTRIC POWER RES INST OF GUANGDONG POWER GRID +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, because the aluminum oxide film formed on the surface of the nanocrystalline layer will cause the lack of aluminum elements, which will affect the structural stability of the nanocrystalline layer
In addition, if the surface α-Al 2 o 3 The film is destroyed, and there is also a lack of sufficient aluminum elements to form an oxide film protective layer again

Method used

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  • Composite coating for gas turbine blade
  • Composite coating for gas turbine blade
  • Composite coating for gas turbine blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] In this embodiment, the MGA1400 superalloy blade used by Mitsubishi Gas Turbine is used as the superalloy substrate 1, and its specific composition (weight percentage) is as follows:

[0026] element

co

Cr

Mo

W

Al

Ti

Ta

C

Zr

wt%

10

14

1.5

4

4

3

5

0.08

0.03

[0027] (Table 1)

[0028] Such as figure 1 , 2 Shown is a gas turbine blade composite coating of the present invention, including MCrAlY layer 2, NiAl layer 3 and nanocrystalline layer 4 coated sequentially on the MGA1400 superalloy blade as a superalloy substrate 1. The thickness of the MCrAlY layer is 100-200 microns, and the MCrAlY layer is prepared by low-pressure plasma spraying or supersonic flame spraying on the surface of the superalloy substrate 1 . The thickness of the NiAl layer is 20-50 microns, the composition of the nano-crystal layer 4 is the same as that of the superalloy substrate 1, the nano-crystal layer 4 is prepare...

Embodiment 2

[0036] Such as image 3 As shown, the difference between this embodiment and Embodiment 1 is that for the superalloy blades of the first two stages, in order to reduce the working temperature and protect the base metal material of the blade, it is also necessary to pass a plasma spraying process on the surface of the nanocrystalline layer 4 Preparation of ZrO 2 Based thermal barrier ceramic coating 5, that is, a composite coating composed of MCrAlY layer 2, NiAl layer 3 and nanocrystalline layer 4 as ZrO 2 The bonding layer of the thermal barrier coating ceramic layer 5, ZrO 2 The thickness of the base thermal barrier ceramic coating 5 is 100-300 microns, and the composite coating at this time is used to improve the bonding force of the thermal barrier coating and improve the high temperature oxidation resistance of the blade.

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Abstract

The invention discloses a novel gas turbine blade composite coating comprising an MCrAlY layer, an NiAl layer and a nanocrystalline layer which are sequentially coated on a gas turbine blade taken as a high-temperature alloy matrix, wherein the nanocrystalline layer has better high-temperature oxidation resistance than that of a conventional MCrAlY layer, and the NiAl layer which is positioned at a middle position is taken as a reserve layer of Al and can be used for providing additional Al elements for the MCrAlY layer and the nanocrystalline layer so as to ensure that aluminum element missing of the nanocrystalline layer caused by aluminum oxide film formation can be avoided, and phase change of the MCrAlY layer caused by oxygen and metal ion diffusion and therefore caused thermal barrier coating falling can also be prevented. A thermal barrier coating is coated on the surface of the nanocrystalline layer, a composite coating consisting of the MCrAlY layer, the NiAl layer and the nanocrystalline layer is taken as a bonding layer of the thermal barrier coating; and the novel gas turbine blade composite coating disclosed by the invention can be used for increasing the bonding power of the thermal barrier coating and improving the high-temperature oxidation resistant property of the blade.

Description

technical field [0001] The invention relates to a composite coating of a gas turbine blade, which can be used as a high-temperature oxidation-resistant coating coating or a bonding layer of a thermal barrier coating for a gas turbine stationary blade and a moving blade, and can improve the high-temperature oxidation resistance of a high-temperature alloy blade. Background technique [0002] my country's rapid economic development has continuously increased the demand for electricity, but the large-scale use of coal-fired steam turbines has a series of problems such as low efficiency and high pollution. The deteriorating environmental pollution in recent years, especially the increasingly serious smog weather, has made it more urgent to replace traditional steam turbines with high-efficiency combined cycle gas turbines. As the core components of gas turbines, the blades usually need to work in high-temperature and high-stress environments, so the superalloy materials used to ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C28/00C23C4/12C23C4/08C23C14/08C23C14/35C23C4/073C23C4/129C23C4/134
CPCC23C14/081C23C14/35C23C28/34
Inventor 黄丰林介东聂铭钟万里王伟李长鹏陈国锋姚志奇
Owner ELECTRIC POWER RES INST OF GUANGDONG POWER GRID
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