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Spraying method of thermal barrier coating with longitudinal cracks for combustion chamber

A technology of longitudinal crack and thermal barrier coating, applied in coating, metal material coating process, fusion spraying and other directions, can solve the problems of short service life, poor thermal cycle resistance, etc. The effect of improving longitudinal damage tolerance and good thermal insulation effect

Inactive Publication Date: 2019-12-31
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The object of the present invention is to provide a kind of spraying method of the thermal barrier coating of band longitudinal crack for combustion chamber, to solve the thermal barrier coating of combustion chamber in the prior art, because ZrO 2 The microstructure of the base ceramic surface layer is lamellar structure, ZrO 2 The base ceramic surface layer is thin, which makes the thermal cycle resistance poor and the technical problem of short service life

Method used

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  • Spraying method of thermal barrier coating with longitudinal cracks for combustion chamber
  • Spraying method of thermal barrier coating with longitudinal cracks for combustion chamber
  • Spraying method of thermal barrier coating with longitudinal cracks for combustion chamber

Examples

Experimental program
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Effect test

Embodiment 1

[0039] A heavy-duty gas turbine was overhauled after 18,000 hours of operation, and it was found that most of the coatings on the combustion chamber parts were peeled off, and thermal barrier coatings needed to be recoated. After the residual coating is removed, adopt the spraying method provided by the invention to restore the coating to the part; the specific steps are:

[0040] (1) Use 46-mesh white corundum sand to roughen the surface of the part to be sprayed;

[0041] (2) Spray the NiCrAlY bonding layer on the area to be sprayed by plasma spraying method, and the thickness of the NiCrAlY bonding layer is 0.25mm;

[0042] What spray NiCrAlY bonding layer adopts is NiCrAlY powder, and the granularity of described NiCrAlY powder is 53 μ m-106 μ m; Described NiCrAlY powder is made up of the component of following percentage by weight: chromium 22.0%, aluminum 9.9%, iridium 1.2%, nickel is margin;

[0043] The spraying process parameters of the NiCrAlY bonding layer are: th...

Embodiment 2

[0054] An aeroderivative gas turbine was overhauled after 9,000 hours of operation, and it was found that most of the coatings on the combustion chamber parts were peeled off, and thermal barrier coatings needed to be recoated. After the residual coating is removed, adopt the spraying method provided by the invention to restore the coating to the part; the specific steps are:

[0055] (1) Use 46-mesh white corundum sand to roughen the surface of the part to be sprayed;

[0056] (2) Spray the NiCrAlY bonding layer on the area to be sprayed by plasma spraying method, and the thickness of the NiCrAlY bonding layer is 0.25mm;

[0057] What spray NiCrAlY bonding layer adopts is NiCrAlY powder, and the particle size of described NiCrAlY powder is 53 μ m-106 μ m; Described NiCrAlY powder is made up of the component of following percentage by weight: chromium 22.5%, aluminum 9.8%, iridium 1.2%, nickel is margin;

[0058] The spraying process parameters of the NiCrAlY bonding layer a...

Embodiment 3

[0069] Spray thermal barrier coating on parts of aero-engine combustion chamber, the specific steps are:

[0070] (1) Use 46-mesh white corundum sand to roughen the surface of the part to be sprayed;

[0071] (2) Spray the NiCrAlY bonding layer on the area to be sprayed by plasma spraying method, and the thickness of the NiCrAlY bonding layer is 0.2mm;

[0072] What spray NiCrAlY adhesive layer adopts is NiCrAlY powder, and the particle size of described NiCrAlY powder is 53 μ m-106 μ m; Described NiCrAlY powder is made up of the component of following percentage by weight: chromium 21.0%, aluminum 11.0%, iridium 0.5%, nickel is margin;

[0073] The spraying process parameters of the NiCrAlY bonding layer are as follows: the nitrogen flow rate is 70 L / min, the hydrogen flow rate is 8.0 L / min, the working current is 500 A, the working voltage is 80 V, the spraying distance is 130 mm, and the powder feeding volume is 45 g / min. min;

[0074] (3) Spray ZrO 2 Base ceramic surfa...

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Abstract

The invention provides a spraying method of a thermal barrier coating with longitudinal cracks for a combustion chamber. The technical problems that in the prior art, a thermal barrier coating for a combustion chamber is poor in heat cycle resistance and short in service life due to the fact that a microstructure of a ZrO2-based ceramic surface layer is of a lamellar structure, and the ZrO2-basedceramic surface layer is thin are solved. The method comprises the following steps that firstly, a NiCrAlY bonding layer is sprayed to a to-be-sprayed area of a part; secondly, after spraying of the NiCrAlY bonding layer is finished, a plasma spraying gun is adopted for preheating the to-be-sprayed area of the part to 370 DEG C to 430 DEG C, after the part reaches the preheating temperature, the plasma spraying method is adopted for spraying the ZrO2-based ceramic surface layer, and during spraying, the spraying distance is 50 mm to 60 mm; and thirdly, after spraying of the ZrO2-based ceramicsurface layer is finished, the part is put into a vacuum furnace to be subjected to heat treatment. The thermal barrier coating has the advantages of being long in service life and good in heat insulation effect.

Description

technical field [0001] The invention relates to the field of manufacture and maintenance of aero-engines and ground gas turbines, in particular to a spraying method of a thermal barrier coating with longitudinal cracks for a combustion chamber. Background technique [0002] In order to increase the combustion temperature of the combustion chambers of aero-engines and ground gas turbines, it is necessary to spray a layer of heat-insulating and thermal-corrosion-resistant thermal barrier coatings inside the combustion chambers. The thermal barrier coating is mainly composed of two layers, namely the bonding layer composed of NiCrAlY and ZrO 2 Base ceramic surface layer, while ZrO 2 The base ceramic finish is the key to thermal insulation and thermal corrosion resistance. [0003] For civil aero-engines or military aero-engines with large bypass ratios, since their service life is longer than that of other small-bypass military aero-engines, the thermal barrier coating used i...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/073C23C4/11C22C19/05
CPCC22C19/058C23C4/073C23C4/11C23C4/134
Inventor 陈永澎余德平郭双全李凯冯云彪程思恩罗春朱晔郭子平
Owner PLA NO 5719 FACTORY
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