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Paper contains an analysis of the 1st stage compressor blade strain distribution. Boundary conditions analysis was presumed for blade clamped in the fatigue holder. Strain distribution verification was performed for blade fundamental frequency. Numerical method results were verified with experimental (strain gauge) method.
Paper presents the description of the Finite Element Method used to determine the first frequency shape of the Turbine Engine compressor blade. Numerical calculations were conducted on blades with damages modelled on the CAD (Computer Aided Design) model at different positions and different depth. Reduced stress and frequency of the damaged and undamaged blades are the results of presented work.
W pracy wykonano symulację metodą elementów skończonych próby czteropunktowego zginania próbki stopu tytanu Ti-6Al-4V z utwardzoną warstwą wierzchnią. W warstwie wierzchniej złożonej z zewnętrznej powłoki sprężystej oraz warstwy dyfuzyjnej wprowadzono pęknięcie powierzchniowe, którego wierzchołek znajdował się w podłożu. Określono wpływ cech geometrycznych i właściwości modyfikowanej warstwy wierzchniej...
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