Adaptive machining and weld repair process
An apparatus and method are provided for an adaptive machining and weld repair process for repairing airfoils, damage to an airfoil leading edge and tip. First, damaged material is machined away from a damaged airfoil edge so as to expose a weld surface. New material is laser deposited on the weld surface so as to create a weld-repaired airfoil having actual dimensions. The actual dimensions of the weld-repaired airfoil are automatically measured using a CMM system so as to generate an actual geometry. The actual geometry is deformed so as to develop a deformation geometry. The component is then machined according to the deformation geometry.
1. A method for restoring a worn edge of an airfoil comprising the steps of:
machining away damaged material from a damaged airfoil edge so as to expose a weld surface;
laser depositing new material on the weld surface so as to create a weld-repaired airfoil having actual dimensions;
automatically measuring the actual dimensions of the weld-repaired airfoil using a CMM system so as to generate an actual geometry;
deforming the actual geometry so as to develop a deformation geometry by:
defining a set of streamlines on an airfoil surface,
defining a set of cross curves that intersect one or more of the streamlines thereby establishing surface points at each such intersection,
associating nominal surface data with each surface point,
defining a set of inspection nominal points that fall on streamlines and cross curves,
measuring an actual blade shape at each inspection nominal point to establish shape deviation data, and
interpolating the shape deviation data with reference to the surface points; and
machining the component according to the deformation geometry.
2. The method according to claim 1 wherein the step of measuring the component further comprises measuring using a coordinate measuring machine.
3. The method according to claim 1 further comprising the step of generating a tool path using machining software.
4. The method according to claim 1 wherein the step of laser depositing new material comprises laser cladding.
5. The method according to claim 1 wherein the step of machining away includes machining the component so as to leave less than 5 thousandths of an inch stock on.
6. The method according to claim 1 further comprising the step of hand finishing the machined component.
7. The method according to claim 1 wherein the steps are performed in the order written.
8. The method according to claim 1 further comprising the step of converting the deformation geometry to a CNC machining data.
9. The method according to claim 1 wherein the step of machining the component further comprises automated machining according to a CNC machining data.
10. The method according to claim 1 wherein the step of machining away damaged material from a damaged airfoil edge comprises machining away a damaged leading edge.
11. The method according to claim 1 wherein the step of machining away damaged material from a damaged airfoil edge comprises machining away a damaged trailing edge.
12. The method according to claim 1 wherein the step of machining away damaged material from a damaged airfoil edge comprises machining away a damaged top edge.
13. A method for restoring a worn edge of an airfoil comprising the steps of:
machining away damaged material from a damaged airfoil edge so as to expose a welding area;
laser depositing new material on the welding area so as to create a weld-repaired airfoil;
defining a set of streamlines on an airfoil surface;
defining a set of cross curves that intersect one or more of the streamlines thereby establishing surface points at each such intersection;
associating nominal surface data with each surface point;
defining a set of inspection nominal points that fall on streamlines and cross curves;
automatically measuring the actual dimensions of the airfoil using a CMM system at each inspection nominal point to establish shape deviation data;
interpolating the shape deviation data with reference to the surface points so as to create a deformation geometry;
converting the deformation geometry to a machine operable code;
machining the component according to the deformation geometry; and
hand finishing the airfoil.
14. The method according to claim 13 wherein the step of machining the component further comprises machining the component so as to leave less than 0.005 inch of material stock on.
15. The method according to claim 13 further comprising the step of transferring the deformation geometry to an automated machining computer.
16. The method according to claim 13 further comprising the step of generating a tool path using machining software.