Automatic preparation method of long-service-life cylinder-like crystal structural thermal barrier coating on surface of guide blade of hot end part of fuel machine

Abstract

The invention relates to an automatic preparation method of a long-service-life cylinder-like crystal structural thermal barrier coating on the surface of a guide blade of a hot end part of a fuel machine. According to the invention, a supersonic flame spray gun and a plasma spray gun are respectively clamped by manipulators; an automatic spraying program is compiled; for a supersonic flame spraying bonding layer, by a main program, a distance from a TCP (Transmission Control Protocol) point to a spray gun orifice is set into 330 to 350mm, a moving speed of the spray gun is set into 500 to 600m/s and a spacing of spraying profiles is set into 20 to 30mm; for a plasma spraying ceramic layer, by the main program, a distance from the TCP point to a spray gun orifice is set into 60 to 70mm, a moving speed of the spray gun is set into 200 to 250m/s, a spacing of spraying profiles is set into 3 to 7mm; in the plasma spraying program compiling process, the trend of each spraying profile is of a shape of a Chinese character 'gong'. The automatic preparation method sequentially comprises the steps of preparation and pretreatment of a matrix, preparation of a bonding layer, preheating of the hot end part and preparation of a ceramic layer; a scanning electron microscope is adopted to observe; the prepared ceramic layer is of a cylinder-like crystal structure; strain tolerance and the thermal shock resistance service life of the coating are obviously improved; compared with the service life of the conventional structural thermal barrier coating, the service life of the coating is obviously prolonged.

Description

technical field [0001] The invention relates to a method for preparing a long-life thermal barrier coating, in particular to an automatic spraying method for preparing a long-life columnar crystal-like structure thermal barrier coating on the surface of a hot end part of a gas turbine. Background technique [0002] Due to the advantages of high efficiency, energy saving and low pollution, gas turbines have been widely used in aviation, ship power, power generation and other fields. In order to obtain higher energy efficiency and greater thrust, the inlet temperature of gas turbine turbines has gradually increased in recent years, and the improvement of material performance and structural design alone cannot meet the rapidly developing application requirements of gas turbines. Thermal barrier coatings have been successfully applied to the protection of aero-engines and heavy-duty gas turbine hot-end components due to their ability to effectively reduce the surface temperature...

AI Technical Summary

Problems solved by technology

Gas turbine working blades are generally prepared by electron beam physical vapor deposition process. The coating has a columnar crystal structure, high strain tolerance, and long service life. The disadvantages are complex preparation process, expensive equipment, high preparation cost, low efficiency, and thin coating. The heat insulation performance is poor, and limited by the volume of the vacuum deposition chamber of the equipment, it is impossible to prepare coatings for large and complex surface components; the guide vanes and other stator components of gas turbines are generally prepared by plasma spraying technology, and the coating structure is a layered structure. Good thermal performance, simple equipment, low preparation cost, high spraying efficiency, but the disadvantages are poor bonding between coating layers, short service life, and the coating preparation method is also manual spraying, and the coating quality is poor in batch stability. Therefore, Conventional structural thermal barrier coatings have been difficult to meet the long-life requirements of ground gas turbines for tens of thousands of hours

[0004] Drawing on the advantages of high strain tolerance of columnar crystal structure coatings and high heat insulatio

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