Identification of Fatigue Wear of Compressor Rotor Blade of a General Electric J85 Turbojet Engine

The paper concerns research and analysis of the technical condition of turbine engine compressor rotor blades. Elements of this type are subjected to variable loads resulting from the occurrence of variable aerodynamic forces and mass inertia. Identification of fatigue damage to compressor rotor blades is important from the point of view of turbine engine reliability and, consequently,flight safety. The object of the research were the first stage compressor blades of the General Electric J85-GE-13B turbojet engine. A method of optical non-contact measurement was used in order to obtain a 3D picture of the blade. Based on this picture and having a CAD model of the blade, it was possible to identify and analyze wear and damages of the blade. The most important novelty of this study is that it constitutes the methodological and metrological basis for the diagnostics of turbine engine compressor rotor components, without the need to dismantle the engine.