High-temperature erosion testing device and method for thermal barrier coating of turbine blade of gas turbine

Abstract

The invention discloses a high-temperature erosion testing device and method for a thermal barrier coating of a turbine blade of a gas turbine. The high-temperature erosion testing device comprises ahigh-temperature spray gun system, a testing system, a cooling system, a central control system and a dust removal system. By using the testing device and the testing method provided by the invention,the high-temperature erosion environment of the turbine blade of the gas turbine in a working state can be simulated to the greatest extent, and the positions and speeds of solid particles impactingthe surface of the thermal barrier coating, and the angles relative to the surface of the coating are simulated, and service environments that after the rebounding of the particles impacting the surface of the thermal barrier coating, other positions of the thermal barrier coating or the surfaces of other blades are impacted in different motion states, and such as multiple times of erosive wear are generated for the coating are simualted. The test result can provide a reliable test basis for researching the service life of the thermal barrier coating, selecting a thermal barrier coating material and the like.

Description

technical field [0001] The invention belongs to the technical field of protective coatings for turbine blades of gas turbines, and in particular relates to a high-temperature erosion test device and method for thermal barrier coatings of turbine blades of gas turbines. Background technique [0002] Thermal barrier coating technology has been widely used in gas turbine turbine blades. By coating the surface of the blade matrix alloy with a high-temperature heat-insulating protective coating, it can reduce the temperature of the matrix alloy, prevent high-temperature corrosion of the blade, prolong the service life of the blade, and improve the efficiency of the gas turbine. . The structure of thermal barrier coating is complex, and the service environment is extremely harsh. During service, not only is it subjected to thermal stress, but also in some cases where combustion is insufficient or blast furnace gas is used as fuel, the solid particles mixed in the gas are accelera...

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Problems solved by technology

However, due to the different sizes of solid particles in the gas, the trajectory and state of the particles in the gas channel are also different. The geometry of the turbine blades is complex and the high-speed rotation causes the position and speed of the solid particles to hit the surface of the thermal barrier coating. And the angles relative to the coating surface are different, and the particles impacting the blade surface will also impact other positions of the thermal barrier coating in different motion states after rebounding, causing multiple erosions and wear on the coating. The above factors are all It is a difficult problem to be solved in simulating the high temperature erosion condition of the thermal barrier coating of the gas turbine blade

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