Method for three-dimensional representation of stratified structure micrometer CT imaging of turbine blade heat barrier coating

Abstract

The invention discloses a method for three-dimensional representation of stratified structure micrometer CT imaging of a turbine blade heat barrier coating. The method comprises the following steps: preparing a double-layer-structure heat barrier coating micrometer CT scanning sample; firstly, carrying out micrometer CT scanning on the heat barrier coating sample, carrying out ring artifact and beam hardening correction on projection data, then carrying out three-dimensional reconstruction to obtain three-dimensional stratified structure information, establishing a three-dimensional structure analysis model, and carrying out characteristic segmentation and extraction on three components, namely a ceramic heat insulating layer, a bonding layer and matrix alloy; then, analyzing the thickness of the coating, extracting the distribution of holes in the coating, calculating the porosity, extracting the interface topography of the coating, and analyzing structure characteristics such as internal defects; and finally, estimating the preparation process quality of the heat barrier coating by integrating the composition, thickness, porosity distribution, interface topography and the like. The method for three-dimensional representation of the stratified structure of the heat barrier coating provided by the invention is suitable for estimation and optimization of the spraying process quality of the heat barrier coating, so that the quality of the heat barrier coating can be well controlled.

Description

Technical field [0001] The invention belongs to a three-dimensional characterization method of coating structure in the non-destructive detection range of a thermal barrier coating of a turbine blade, and specifically is a three-dimensional characterization method of a micron CT imaging of a layered structure of a thermal barrier coating of a turbine blade. Background technique [0002] The working conditions of aero-engine turbine blades are very harsh. They are not only scoured by high temperature, high pressure, and high-speed airflow, but also subjected to huge centrifugal force, aerodynamic force, thermal stress, alternating force and random load. As the combustion temperature, thrust-to-weight ratio and thermal efficiency of the engine increase, the working conditions of the engine turbine blades, especially the gas temperature in the combustion chamber, have reached 1700℃-1800℃, causing the service temperature of the turbine blades to reach or exceed that of superalloy and ...

AI Technical Summary

Problems solved by technology

In 2005, Ramesh mentioned in the patent application (7298818) the idea of ​​constructing a CT imaging system to detect the microstructure inside the thermal barrier coating, but the reconstruction effect of the conventional micro-CT system is not ideal

[0005] Although the three-dimensional structural information of thermal barrier coatings can be obtained by micro-CT at present, the signal-to-noise ratio of the reconstructed image is not high, and the reconstructed image is seriously affected by beam hardening artifacts, which seriously interfere with the three-dimensional segmentation accuracy, and the bonding layer and Insufficient contrast between the base alloys makes it difficult to separate the bond coat from the base alloy

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