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Early detection of cracks in turbine aeroengine compressor blades

Szczepanik R.

Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka

1999

nr 115

361--370

Problem of early detection of rotor blades cracks is particularly important for flight safety and economy. An early detection of fatigue root cracks in first stage compressor blades is of a great importance for flight safety due to dimensions and mass of blades. The broken blade causes as a rule the engine break-down, which in case of an one-engined aircraft night be a formidable danger to the pilot. Some results of investigations and devices which enable an relatively early detection of compressor blade cracks in an airborne engine as well as keeping the crew informed of this fact in order to get safety to the homebase are discussed and presented in this paper.

System for inflight early detection of cracks in turbine aero-engine compressor blades

Szczepanik R.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

1999

nr 9

139-144

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. The structure of a computer-based aero-engine compressor blades has been discussed and presented in this paper.