Abstract
A phenomenon of dynamic change of an aero-engine compressor blades natural frequency in course of fatigue cracks propagation in their roots /on the example of a Polish turbojet engine/ is described. On the ground of this phenomenon main working principles of a device, which measures vibrations of turbine engine rotor blades with application of the noninterferent discretephase method /MDPh/, used for early detection of first stage compressor blade cracks are discussed.
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