Abstract

The structure of a conditio monitoring system to diadnose some turbojet engines has been discussed in the paper. System approach to the actual technical problem has been exemplified with the fatigue crack growth within the first stage compressor blades. Results of statistical analysis of the proces of blades fatigue cracking have issuedand followed with a concept of solving the problem. An optimum measuring method has been suggested as well. The method of measuring precisely the engine rotational speed and amplitude of vibration of the first-stage compressor blades has also been discussed. Results of numerical analysis of measurements have also been enclosed. The application of only one measuring line to complex, dynamic diagnostic of the engine technical condition of the engine fuel and bearing system. The operational experience gained in the course of implementing the diagnostic system into the Air Force of the Republic of Poland is also presented.