Development of a Touch Probing System for Gaging the Compressor Blades of the GTE

Abstract

The article describes the touch probing system with the strain gage as the main measuring element. The device has small geometric dimensions and it was developed to measure the gas turbine engine compressor blades. To select the optimum configuration of the probing system, mathematical models of two principal configurations were developed. Simulation modeling of the force of the measured surface impact on the measuring tip was carried out in the Ansys environment for these assemblies. On the basis of practical experiments, the diagram of the deviation of the probe on the resistance of the strain gage was constructed. Reference element were measured to determine the accuracy of the designed touch probing system.

Experimental Study of Energy-Power Parameters of Billet Rolling of Compressor Blades of Aircraft Engines

“…This part is the most massive part of a gas turbine engine, and its geometry determines the performance of the gas turbine engine as a whole. The perfection of compressor blades aerodynamic process is determined by the level of profiling during design and the accuracy of their manufacturing achieved in production [6][7][8][9]. The resulting geometry of compressor blades is determined by the following factors: accuracy of transfer of theoretical surface model to the forming equipment, its technological capabilities, accuracy and rigidity of used tooling, perfection of the technological process of manufacturing and measuring the part.…”