Integration of the Results of the Control and Measurement of Blade Airfoil into the Computational Study of the Fan Stage Workflow

As a part of development of the methodology for optimizing the design of fan stages, a procedure has been implemented for integrating the results of control and measurement of the geometry of the blades into a computational study of the workflow of an aircraft engine. The methodology of control and measurement of the blade airfoil and the algorithm for processing and converting data obtained by the measurement are presented for their subsequent use in creating the parametric the 3D-models of “cold” and “hot” shaped blades designed for numerical simulation of the stress-strain state of individual blades, as well as for analyzing the aerodynamic characteristics of the fan stage.