Systems and methods for pre-stressing blades
AssigneeUnited Technologies Corporation
InventorCharles H. Roche
Life of this patent
Estimating the term…
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.
Claims19
A method for pre-stressing a compressor blade or a fan blade of a gas turbine engine, the method comprising:
- pre-stressing the compressor blade or the fan blade by rotating the compressor blade or the fan blade relative to an axis;
- and
- controlling rotational speed of the compressor blade or the fan blade to generate residual stress in the compressor blade or the fan blade, wherein the pre-stressing applies loads to or stresses to the compressor blade or the fan blade before the compressor blade or the fan blade is used or operated in an intended application.
A method for pre-stressing compressor blades or fan blades of a gas turbine engine, the method comprising:
- pre-stressing the compressor blades or the fan blades by rotating the compressor blades or the fan blades relative to an axis;
- and
- controlling rotational speed of the compressor blades or the fan blades to generate residual stress in the compressor blades or the fan blades, wherein the compressor blades or the fan blades are located on a plurality of fan blade units, and the pre-stressing applies loads to or stresses to the compressor blades or the fan blades before the compressor blades or the fan blades are used or operated in an intended application.
A system for pre-stressing compressor blades or fan blades of a gas turbine engine, the system comprising:
- a rotation unit configured to rotate and pre-stress a compressor blade or a fan blade relative to an axis;
- and
- a control unit configured to control rotation speed of the compressor blade or the fan blade to generate residual stress in the compressor blade or the fan blade, wherein pre-stress of the compressor blade or the fan blade applies loads to or stresses to the compressor blade or the fan blade before the compressor blade or the fan blade is used or operated in an intended application.
Dependencies are inferred from the claim text.