Methods and apparatus for reducing vibrations induced to airfoils

摘要

Methods and apparatus for fabricating a rotor blade (40) for a gas turbine engine are provided. The rotor blade includes an airfoil (42) having a first sidewall (44) and a second sidewall (46), connected at a leading edge (48) and at a trailing edge (50). The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length (53) C, a respective maximum thickness (58) T, and a maximum thickness to chord length ratio (T max /C ratio), forming the root portion having a first T max /C ratio, forming the tip portion having a second T max /C ratio, and forming a mid portion (57) extending between a first radial span and a second radial span having a third T max /C ratio, the third T max /C ratio being less than the first T max /C ratio and the second T max /C ratio.