Systems and methods for pre-stressing blades
AssigneeUnited Technologies Corporation
InventorCharles H. ROCHE
Life of this patent
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Abstract
A system and methods are provided for pre-stressing blade elements for a gas turbine engine. In one embodiment, a method includes rotating a blade element relative to an axis. The method may also include controlling rotational speed of the blade element to generate residual stress in the blade element. The method may also include rotating multiple blade elements and fan blade units to generate residual stress. Blade elements may be rotated to exceed a maximum operating speed of the blade element to 120% of the maximum operating speed of the blade element.
Claims17
A method for pre-stressing a component for a gas turbine engine, the method comprising:
- rotating the component relative to an axis;
- and
- controlling rotational speed of the component to generate residual stress in the component.
A system for pre-stressing blade elements for a gas turbine engine, the system comprising:
- a rotation unit configured to rotate a blade element relative to an axis;
- and
- a control unit configured to control rotation speed of the blade element to generate residual stress in the blade element.
Dependencies are inferred from the claim text.