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The location parameters of the actual profile of the blades of a gas turbine engine relative to its nominal position are used to assess the quality of these parts manufacture. The complex shape of the aerodynamic surfaces of the blades, as well as the errors in their manufacture make it difficult to unambiguously determine the displacement and rotation of the actual profile. The use of various methods for calculating the parameters under consideration may result in mismatching values, which raises the question of a reasonable choice of the methods used. This paper presents two methods for determining the geometric parameters of the location of the aerodynamic profiles of the blades, taking into account the features of their manufacture and the requirements of the existing industry standard. Also, the work evaluated the effectiveness of the proposed methods in determining the processing parameters of the blades of a gas turbine engine.

Methods for determining the location parameters of GTE blade profiles based on their measurement results