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Ceramic thermal barrier coating on surface of metal base body and application of ceramic thermal barrier coating in engine

A technology of thermal barrier coatings and metal substrates, applied in metal material coating technology, engine components, combustion engines, etc., can solve problems such as increasing hydrocarbon and carbon monoxide emissions, carbon deposits, automatic ignition, and early combustion

Active Publication Date: 2020-09-15
上海亚域动力工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although low-cetane fuel has a high compression self-ignition temperature, the ignition temperature and ignition energy on the fuel surface are relatively low, which can easily lead to automatic ignition of carbon deposits on pistons, exhaust valves or cylinder heads, resulting in premature combustion and increased carbon Emissions of hydrogen compounds and carbon monoxide

Method used

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  • Ceramic thermal barrier coating on surface of metal base body and application of ceramic thermal barrier coating in engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] Such as figure 1 As shown, the MCrAlY bonding layer and the TBC top layer are sprayed on the turbine casing by atmospheric plasma spraying. The specific composition of the MCrAlY bonding layer is 37.0wt% Co content, 21.8wt% Cr content, 9.36wt% Al content, and 0.52% Y content wt%, Ni balance. The specific composition of the top layer of TBC is Y 2 o 3 Content 7wt%, Zr 2 o 3 margin. The thickness of the coating is uniform, the thickness of the MCrAlY bonding layer is 0.184mm, and the thickness of the TBC top layer is 0.095mm.

[0042] Due to the chemical combination between the coating and the substrate, the bonding strength is improved. In this embodiment, the bonding strength between the TBC top layer and the substrate at room temperature is 36MPa.

[0043] The MCrAlY bonding layer is located between the base metal and the thermal barrier ceramic surface layer, which has the dual functions of improving the physical compatibility of the coating and the base and ant...

Embodiment 2

[0046] Spray the bonding layer and the top layer on the turbine casing by cold spraying. The specific composition of the bonding layer is chromium magnesium phosphate binder content 43wt%-71wt%, spherical aluminum powder content 5wt%-15wt%, flake Aluminum powder content 7wt%-13wt%, Cr 2 o 3 The content is 16wt%-30wt%. The specific composition of the top layer is γ-Al 2 o 3 The content is 6wt%-14wt%, the chromium magnesium phosphate binder content is 67wt%-91wt%, and the BN content is 1wt%-8wt%. The thickness of the coating is uniform, the thickness of the bonding layer is 20-60um, and the thickness of the top layer is 10-50um.

[0047] In this embodiment, the bonding strength between the top layer and the substrate at room temperature is 35.5 MPa.

[0048] The bonding layer is between the turbine casing and the top layer, and has the effect of improving the physical compatibility, oxidation resistance and corrosion resistance of the coating and the substrate.

[0049] Th...

Embodiment 3

[0052] The bonding layer and the top layer are sprayed on the turbine casing by cold spraying. The specific composition of the bonding layer is 40wt%-65wt% of chromium magnesium phosphate binder, 7wt%-12wt% of spherical aluminum powder, flake Aluminum powder content 5wt%-16wt%, Cr 2 o 3 The content is 10wt%-33wt%. The specific composition of the top layer is γ-Al 2 o 3 Content 4wt%-24wt%, SiO 2 .nH 2 The O content is 60wt%-90wt%. The thickness of the coating is uniform, the thickness of the bonding layer is 10-70um, and the thickness of the top layer is 20-65um.

[0053] In this embodiment, the bonding strength between the TBC top layer and the substrate was tested at room temperature to be 35 MPa.

[0054] The bonding layer is located between the turbine casing and the top layer, and has the effect of improving the physical compatibility, oxidation resistance and corrosion resistance of the coating and the substrate. The thermal conductivity of the ceramic thermal barr...

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Abstract

The invention discloses a ceramic thermal barrier coating on the surface of a metal base body and application of the ceramic thermal barrier coating in an engine, and belongs to the technical field ofceramic coatings. A bonding layer and the ceramic thermal barrier coating are sequentially prepared on the surface of the metal base body, wherein the preparation raw material of the ceramic thermalbarrier coating is Y2O3 powder and Zr2O3 powder, or the preparation raw material of the ceramic thermal barrier coating is gamma-Al2O3, a chromium magnesium phosphate binder and BN powder, or the preparation raw material of the ceramic thermal barrier coating is gamma-Al2O3 and SiO2. nH2O; and the ceramic thermal barrier coating is further coated with an oxidation catalyst, and the porosity of theoxidation catalyst is larger than that of the bonding layer. According to the ceramic thermal barrier coating on the surface of the metal base body and the application of the ceramic thermal barriercoating in the engine, the prepared ceramic thermal barrier coating is applied to the engine, and the oxidation catalyst added in the ceramic thermal barrier coating can utilize excessive hydrocarbonand carbon monoxide and oxidize the hydrocarbon before the hydrocarbon is converted into deposited carbon, so that the fuel enrichment during cold start is reduced, the emission of the hydrocarbon andthe carbon monoxide is reduced, and the preignition phenomenon caused by carbon deposition can be prevented.

Description

technical field [0001] The invention relates to the technical field of ceramic coatings, in particular to a ceramic thermal barrier coating on the surface of a metal substrate and its application in engines. Background technique [0002] In order to improve the efficiency of the engine or gas turbine and reduce carbon emissions, its combustion temperature is required to be higher and higher. However, the excessively high temperature brings a more severe service environment to the metal parts of the heat engine, and the ordinary single crystal or superalloy has reached the limit of use. , it is difficult to meet the requirements. To solve this problem, thermal barrier coating technology has been widely used in recent years. Ceramic thermal barrier coatings have the functions of heat insulation, wear resistance, corrosion resistance and oxidation resistance, and are widely used in aerospace, aviation and energy fields, especially in high-pressure turbine blades, combustion ch...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/11C23C4/073C23C4/04C23C4/134F01D5/28F01D25/00F01L3/04F01N13/16F02B23/00F02F1/24F02F3/14B01J23/63B01J37/02
CPCC23C4/11C23C4/073C23C4/134C23C4/04F02F3/14F01L3/04F02F1/24F02B23/00F01N13/16F01D25/005F01D5/284F01D5/28B01J37/0234B01J23/63Y02T10/12
Inventor 于昊君孙惠民
Owner 上海亚域动力工程有限公司
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