Abstract
X-ray computed tomography is more often applied in non-destructive testing the quality of construction elements significantly crucial for reliability and safety of device elements, machines and complex industrial systems. This article describes the computed tomography (CT) system used to inspect the technical condition of turbine blades of the aircraft engine. The impact of the experimental conditions on the correctness of the obtained results was determined. The appropriate selection of parameters for the experiment was given, and the correct test results of gas turbine blades were presented. Failures, manufacturing defects, material deviations of nickel-cobalt alloyed blades were identified. The thickness of walls was measured in the selected cross-sections with the accuracy of 0.01 mm, and selected manufacturing defects of cooling passages were diagnosed. It was demonstrated that the application of the CT system allows for detailed non-destructive inspection of the technical condition of machine parts. The test results proved that the X-ray computed tomography could be applied in the production and repairs of machines.
Highlights
IntroductionThe turbine blade is one of the most important components of a turbine engine due to the reliability of operation and safety of the engine and the aircraft
The reliability and service life of the blade is significantly influenced by internal defects of various origin and type, such as structure thinning, micro-cracks, the incorrect shape of the interior, thermal barrier coating (TBC) delamination, etc
The reconstructed cross-sectional image is a quantitative map of an X-ray linear absorption coefficient in voxels that make up the scanned layer
Summary
The turbine blade is one of the most important components of a turbine engine due to the reliability of operation and safety of the engine and the aircraft. The reliability and service life of the blade is significantly influenced by internal defects of various origin and type, such as structure thinning, micro-cracks, the incorrect shape of the interior, thermal barrier coating (TBC) delamination, etc. A categorization of defects and their causes is presented in [1]. Frequent causes of failure are unfavorable changes in the structure of blades, induced by excessive temperature and operation time as well as the chemical impact of exhaust gases: Licensee MDPI, Basel, Switzerland.
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