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Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof

A technology for bonding the bottom layer and sealing the coating. It is applied in the direction of coating, metal material coating technology, and high-efficiency propulsion technology. Matching and other problems, to achieve the effect of increasing the bonding strength, small particle size of raw materials, and fine and dense tissue

Active Publication Date: 2020-12-08
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to solve the problems of the existing high-temperature sealing coating layer mismatch, poor bonding, poor erosion resistance and scratch resistance, and large-scale peeling off of the coating, the invention provides a double-layer anti-oxidation bonding bottom high-temperature seal Strict coating and its preparation method, using CoNiCrAlY system materials with two particle sizes to spray anti-oxidation primer and intermediate bonding coating, using ZrO containing hexagonal boron nitride and polyester 2 ·Y 2 o 3 The ceramic system material is sprayed with an abradable sealing surface layer, and a double-layer CoNiCrAlY alloy coating is prepared by using a low-pressure plasma spraying process to obtain a high-temperature sealing coating system with a three-layer structure, which can greatly improve the tensile bonding strength

Method used

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  • Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof
  • Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof

Examples

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Embodiment 1

[0030]A double-layer anti-oxidation bonding primer high-temperature sealing coating, including CoNiCrAlY anti-oxidation primer, CoNiCrAlY intermediate bonding transition layer and ZrO 2 ·Y 2 o 3 Ceramic sealing layer;

[0031] The CoNiCrAlY anti-oxidation bottom layer has an element mass percentage of: Ni32%, Cr21%, Al8%, Y0.5%, and the balance is Co; the thickness of the CoNiCrAlY anti-oxidation bottom layer is 0.10mm; the structure of the CoNiCrAlY anti-oxidation bottom layer The porosity is 0.6%; the raw material of the CoNiCrAlY anti-oxidation bottom layer is Co32Ni21Cr8Al0.5Y powder with a particle size of 10 μm;

[0032] The CoNiCrAlY intermediate bonding transition layer, the element mass percentage is: Ni32%, Cr21%, Al8%, Y0.5%, the balance is Co; the thickness of the CoNiCrAlY intermediate bonding transition layer is 0.15mm; the CoNiCrAlY intermediate The tissue porosity of the bonding transition layer is 0.8%; the raw material of the CoNiCrAlY intermediate bonding...

Embodiment 2

[0045] A double-layer anti-oxidation bonding primer high-temperature sealing coating, including CoNiCrAlY anti-oxidation primer, CoNiCrAlY intermediate bonding transition layer and ZrO 2 ·Y 2 o 3 Ceramic sealing layer;

[0046] The CoNiCrAlY anti-oxidation bottom layer has an element mass percentage of: Ni32%, Cr21%, Al8%, Y0.5%, and the balance is Co; the thickness of the CoNiCrAlY anti-oxidation bottom layer is 0.08mm; the structure of the CoNiCrAlY anti-oxidation bottom layer The porosity is 0.65%; the raw material of the CoNiCrAlY anti-oxidation bottom layer is Co32Ni21Cr8Al0.5Y powder with a particle size of 25 μm;

[0047] The CoNiCrAlY intermediate adhesive transition layer has an element mass percentage of: Ni32%, Cr21%, Al8%, Y0.5%, and the balance is Co; the thickness of the CoNiCrAlY intermediate adhesive transition layer is 0.14mm; the CoNiCrAlY intermediate The tissue porosity of the bonding transition layer is 0.73%; the raw material of the CoNiCrAlY intermedi...

Embodiment 3

[0060] A double-layer anti-oxidation bonding primer high-temperature sealing coating, including CoNiCrAlY anti-oxidation primer, CoNiCrAlY intermediate bonding transition layer and ZrO 2 ·Y 2 o 3 Ceramic sealing layer;

[0061] The CoNiCrAlY anti-oxidation bottom layer has an element mass percentage of: Ni32%, Cr21%, Al8%, Y0.5%, and the balance is Co; the thickness of the CoNiCrAlY anti-oxidation bottom layer is 0.11 mm; the tissue pores of the CoNiCrAlY anti-oxidation bottom layer The ratio is 0.7%; the raw material of the CoNiCrAlY anti-oxidation bottom layer is Co32Ni21Cr8Al0.5Y powder with a particle size of 5.5 μm;

[0062] The CoNiCrAlY intermediate bonding transition layer, the element mass percentage is: Ni32%, Cr21%, Al8%, Y0.5%, the balance is Co; the thickness of the CoNiCrAlY intermediate bonding transition layer is 0.12mm; the CoNiCrAlY intermediate The tissue porosity of the bonding transition layer is 0.8%; the raw material of the CoNiCrAlY intermediate bond...

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Abstract

The invention discloses a double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and a preparation method thereof, and belongs to the technical field of aero-engine coatings. The double-layer anti-oxidation bonding bottom layer high-temperature sealing coating structurally comprises a CoNiCrAlY anti-oxidation bottom layer, a CoNiCrAlY middle bonding transition layer anda ZrO2.Y2O3 ceramic sealing layer. CoNiCrAlY system materials with two particle sizes are adopted to spray the anti-oxidation bottom layer and the middle bonding coating, ZrO2.Y2O3 ceramic system materials containing hexagonal boron nitride and polyester are adopted to spray a wearable sealing surface layer, the high-temperature sealing coating is obtained, the bonding strength can be improved by10MPa or above, the high-temperature oxidation resistance can be improved by 15% or above, and the thermal cycle life can be prolonged by 25% or above; and the problems that layers of an existing high-temperature sealing coating are not matched, the bonding performance is poor, the erosion resistance and the scraping resistance are poor, and large coating blocks are peeled off are solved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine coatings, in particular to a double-layer anti-oxidation bonding bottom high-temperature sealing coating and a preparation method thereof. Background technique [0002] During the working process of the engine, in order to prevent mechanical damage caused by friction between the tip of the rotating turbine blade and the casing under various conditions, a certain gap is reserved between the surface of the turbine blade and the casing. However, the existence of radial clearance has a great influence on the operation of the turbine. When the sealing leakage flow is reduced by 1%, the thrust of the engine can be increased by 1%, and the fuel consumption rate can be reduced by 0.1%, so it is necessary to prepare a high-temperature abradable sealing coating on the inner surface of the outer ring block of the turbine. [0003] The high temperature sealing coating system must have excellent high temp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/11C23C4/073C23C4/134C23C4/137
CPCC23C4/11C23C4/073C23C4/134C23C4/137Y02T50/60
Inventor 张佳平李明康芦国强李浩宇袁福河彭新
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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