Blade for a turbine engine and method to prevent the crack propagation in a blade for a turbine engine

摘要

In the area of a gas turbine blade's (31) front edge (39), a slot (51) parallel to the blade's axis (30) limits crack propagation in an axial direction by starting from the gas turbine blade's front edge. The slot has a clearance from the gas turbine blade's front edge of less than twenty-five percent of a section cord length. It also has a length of twenty percent of the blade's height. An independent claim is also included for a method for preventing crack propagation in a gas turbine blade.