Differential excitation eddy current sensor testing for aircraft engine blades defect

The micro-crack detection experiments of the certain model aircraft engine turbine blades were carried out. Based on eddy current testing technology, a small differential excitation probe with high sensitivity and difference from traditional probes was designed and developed. The simulation analysis of micro-crack on aircraft engine turbine blades was completed by finite element analysis software. In order to realize the automatic and efficient detection of engine blades, a computerized numerical control (CNC) scanner with multi-degree of freedom was designed and adopted to control the acquisition process. The detection signals were acquired via the signal conditioning circuit, A/D card and input into computers, where the signals storing, processing and output completed. By comparing the experimental and simulation results, it can be seen that the difference incentive eddy current sensor can effectively and accurately determine the micro-crack position on the blade surface and has practical significance and reference value for evaluating micro-defects of aircraft turbine blade parts during early diagnosis.