The first stage blades of a heavy-duty gas turbine compressor are newly independently developed and designed, which use the advanced 3D modeling technology to design high-performance blade profiles. It is necessary to master the blades’ vibration characteristics to verify the reliability of the blades. The finite element method was used to analyze the vibration frequency of the blades under dynamic frequency testing conditions and actual operating conditions. Meanwhile, the radio telemetry technology has been introduced to verify the dynamic frequency of the blade. The dispersion effects caused by blade material and processing tolerances, as well as assembly tolerances were also considered. The results indicate that the theoretical analysis of blade vibration is consistent with the test characteristics, with a deviation of no more than 1.2%. The theoretical frequency avoidance margin of compressor blades under operating conditions can meet the deviation between numerical analysis methods and experimental testing methods, as well as the frequency influence caused by material, processing, and assembly factors, and still have a large safety margin. The research results provide guidance for the development of gas turbine compressor blades, as well as the upgrading, improvement, and vibration monitoring of blades throughout their entire lifecycle.