Method for producing aerodynamically optimized contour of leading edges of gas turbine blade, involves digitization of leading edge of gas turbine blade and detecting trailing edge of gas turbine blade

摘要

The method involves digitization of the leading edge of the gas turbine blade and detecting the trailing edge of the gas turbine blade. The rotation and the chord length of the digitized leading edge and the detected trailing edge of the gas turbine blade are calculated. An aerodynamically optimized contour is calculated starting from the master-set-contour under consideration of the rotation and chord length. The motion sequence of the difference between the actual contour and aerodynamically optimized contour is calculated. An independent claim is included for an arrangement for producing an aerodynamically optimized contour of the leading edge of a gas turbine blade.