Preparation method of thermal barrier coating with composite structure

A technology of thermal barrier coating and composite structure, which is applied in the direction of coating, superimposed layer plating, metal material coating process, etc., can solve the problems of complex process, high cost, poor shielding effect, etc., and achieve high design flexibility , Improve the effect of resisting foreign object erosion and prolonging the service life

Pending Publication Date: 2022-06-21
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The coating process for tooling shielding has disadvantages such as complicated procedures, poor shielding effect, and high cost

Method used

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  • Preparation method of thermal barrier coating with composite structure
  • Preparation method of thermal barrier coating with composite structure
  • Preparation method of thermal barrier coating with composite structure

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preparation example Construction

[0027] The present invention proposes a preparation method of a thermal barrier coating with a composite structure. The thermal barrier coating can be deposited on the surface of a superalloy part coated with an adhesive layer, such as NiPtAl, MCrAlY, etc. which are currently mainstream. The layered ceramic layer material can use the current conventional fluorite structural materials (such as yttria-stabilized zirconia (YSZ)), pyrochlore structural materials (such as gadolinium zirconate, lanthanum ceric acid), etc., using plasma spraying combined with laser coaxial transmission. Powder deposition is realized, which specifically includes the following steps:

[0028] S1, coating an adhesive layer on the surface of the alloy substrate; the adhesive layer can be prepared by plasma spraying, low pressure plasma spraying, supersonic spraying, EB-PVD, vapor aluminizing deposition and chemical vapor deposition.

[0029] S2, the plasma sprayed lower layered structure, and the thickne...

Embodiment 1

[0038] A preparation method of thermal barrier coating with composite structure adopts the following steps:

[0039] S1, coating the NiCoCrAlY bonding layer on the surface of the alloy substrate;

[0040] S2, plasma sprayed lower layered structure, using 8YSZ material;

[0041] S3, the upper layer columnar structure is deposited by laser coaxial powder feeding, and the number of deposition layers is one layer. First, control the movement of the robotic arm to adjust the positioning and focusing size of the laser head on the surface of the coated workpiece; use 15-45μm spherical granulation 8YSZ powder, 4-way coaxial powder feeding, and the carrier gas volume is 7L / min; turn on the pulsed laser and continuously feed powder and ensure that the powder is fed into the laser beam; the laser beam power is 100W, and the beam spot size is 200μm; the robotic arm is controlled to make the laser head move continuously on the surface of the workpiece to achieve columnar coating depositio...

Embodiment 2

[0044] A preparation method of thermal barrier coating with composite structure adopts the following steps:

[0045] S1, coating the NiPtAl bonding layer on the surface of the alloy substrate;

[0046] S2, plasma sprayed lower layered structure, using 8YSZ material;

[0047] S3, the upper layer columnar structure is deposited by laser coaxial powder feeding, and the number of deposition layers is 3 layers. First control the movement of the robotic arm, adjust the positioning and focusing size of the laser head on the surface of the coated workpiece; use 15-45μm spherical granulation Gd 2 Zr 2 O 7 Powder, 4-way coaxial powder feeding, the carrier gas volume is 5L / min; Turn on the pulsed laser, continuously feed powder and ensure that the powder is sent into the laser beam; The laser beam power is 150W, and the beam spot size is 250μm; The head continuously moves on the surface of the workpiece to realize the deposition of the columnar coating, and the laser pulse output is ...

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Abstract

The invention discloses a preparation method of a thermal barrier coating with a composite structure. The preparation method comprises the following steps: S1, coating the surface of an alloy matrix with a bonding layer; s2, performing plasma spraying on a lower layered structure, wherein the thickness of the layered structure is 100-200 [mu] m; and S3, laser coaxial powder feeding deposition is conducted on an upper-layer columnar crystal structure, the number of deposition layers is 1-10, the thickness of the columnar crystal structure is 100-1000 microns, the diameter of columnar crystals is 100-500 microns, and the gap between the columnar crystals is 10%-20% of the thickness of the upper-layer columnar crystal structure. The method is simple in process, low in raw material cost and process cost and high in design flexibility, and local coating of the surface of a complex part can be achieved; the prepared layered-columnar crystal double-layer structure thermal barrier coating has good thermal cycle resistance and erosion resistance.

Description

technical field [0001] The invention relates to the technical field of thermal barrier coatings, in particular to a method for preparing thermal barrier coatings with composite structures on the surfaces of hot end components such as aero-engines, gas turbines, piston-diesel turbine blades, and guide blades. The method can coat a thermal barrier coating with a layered-columnar composite structure on the surface of the component as a whole or locally. Coating for higher thermal cycle life and erosion resistance. Background technique [0002] Electron beam physical vapor deposition (EB-PVD) and plasma spraying (PS) are currently the mainstream technologies for thermal protection of aero-engine and gas turbine hot-end components, especially for guide blades and high-pressure turbine blades. Among them, the plasma spray coating has lower cost, has a layered structure and better thermal insulation performance. The EB-PVD thermal barrier coating consists of columnar crystals per...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C24/10C23C28/00
CPCC23C4/134C23C24/10C23C28/00Y02T50/60
Inventor 彭徽郭洪波宫声凯
Owner BEIHANG UNIV
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