SYSTEM AND METHOD FOR PRE-STRESSING BLADES

摘要

A system (100; 500) and method are provided for pre-stressing blade elements (105 1-n ; 200) for a gas turbine engine. In one embodiment, a method includes rotating a blade element (105 1-n ; 200) relative to an axis (120; 520) and controlling rotational speed of the blade element (105 1-n ; 200) to generate residual stress in the blade element (105 1-n ; 200). The method may also include rotating multiple blade elements (105 1-n ; 200) and fan blade units (505 1-n ) to generate residual stress. Blade elements (105 1-n ; 200) may be rotated to exceed a maximum operating speed of the blade element (105 1-n ; 200) to 120% of the maximum operating speed of the blade element (105 1-n ; 200).