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Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine

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Academic year: 2019

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Fig. 1. Experimental setup to measure the dynamic properties of the structure.
Fig. 3. FRF magnitude and phase of H 1,2 .
Fig. 5. Numerical model of the three dof system under seismic excitation.
Fig. 6. Comparison between experimental and updated FRFs.

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