| Abstract:In order to solve the problems of lacking effective inspection means and poor consistency of measurement results for
aeroengine turbine blade film cooling hole geometrical feature parameters, an inspection system for turbine blade film cooling holes was
designed and established based on fiber optic-based multi-sensor measurement technique. The measurement method of the film cooling
holes using the system was proposed, and verified by measurement practices. The system is a multi-sensor measurement system with the
ability of contact and non-contact measurement, spatial attitude positioning, and 3D projection, realizing measurement of film cooling holes
over the entire turbine blade. A high-pressure turbine blade was selected for conducting the film cooling hole measurement by using the
measurement system. Accurate geometrical feature parameters of the film cooling holes were calculated, including their diameters, axis
angles, and position. The results show that through measurement uncertainty analysis and evaluation, uncertainties of the diameters and the
positions are both less than 0.01mm, which fully meets the accuracy requirements of the measuring instrument derived from the design
tolerances, and the system can be used for the inspection of the film cooling hole of the turbine blade. |
