General Electric Company
AIRFOIL FOR A TURBINE ENGINE

Abstract:

A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.