Development of a design methodology for a specialized measuring probe for stationary gas turbine unit axial compressors traversing. Providing Experiments to evaluate the qualitative and quantitative characteristics of the probe. On the basis of the potential flow around the cylinder and the gas-dynamic similarity, the main characteristics of the probe are investigated. Verification of numerical modeling is performed for the various calculation of the measuring probe. Based on aeromechanical optimization of the probe design, an assessment of the permissible immersion depth into the flow path is carried out. The optimal design configuration of the probe is also determined by the quantitative value of the maximum equivalent stresses. Recommendations for determining the diameter of the probe and the position of the measuring holes were obtained. The optimal configuration design of the probe has been determined. As a result of the work, an experimental stand was designed and manufactured. The use of the stand made it possible to carry out measurements in 11 sections between the blade rows with the number of measurement parameters points parameters in height up to 200 in one section. It was possible to provide measurements with a step up to 0.1 mm and a positioning accuracy in the radial position of +/- 0.025 mm and an accuracy of setting the angle from +/- 0.7 degrees to +/- 3 degrees, depending on the section.