High Cycle Fatigue (HCF) cracks generated by blade vibration are a common source of failure in gas turbine engines. In-situ detection of blade vibration helps operators avoid engine speeds that are critical and helps infer the initiation of cracks via a change in the resonance characteristics of blades. This paper presents the results of dynamic investigations carried out on a Low Pressure Turbine (LPT) rotor through numerical and experimental analyses. In order to meet the mechanical requirements during the development phase, a numerical tool based on finite element analysis (FEA) and an experimental tool based on non-intrusive measurement technique were used. The rotor stage was characterized from resonance perspective by measuring the blade vibration frequencies, amplitudes and the rotational speed of the rotor with small proximity sensors mounted around the turbine casing. The intention was to ensure that the blade design has no critical resonances that interfere with fundamental engine orders in the operating speed range of interest. A Campbell diagram generated using the measured resonances was in good agreement with the predictions. The vibration characteristics ascertained were amplitudes, frequencies, damping and static position of all blades for identifying the initiation of cracks. Detailed analyses were performed to identify the possible causes of failures by observing the anomalies in the blade vibration behaviour and examination of foiled blades.