Method of machining airfoils by disc tools
AssigneePratt & Whitney Canada Corp.
InventorsMarc Lorenzo Campomanes, Charles Edward Becze, Bastien Ste-Marie
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Abstract
A method for machining a rotor having a disc and a plurality of integral airfoils projecting outwardly from the disc, according to one aspect of the invention, comprises a step of machining each airfoil with a disc tool having a grinding periphery thereof adapted for removing material from the airfoils. The grinding periphery has a thickness greater than a thickness of an adjacent supporting portion of the disc to permit the grinding periphery to pass a surface of an airfoil in a multi-axis simultaneous motion, thereby matching the grinding periphery with a predetermined geometry of a portion of the airfoil.
Claims15
A method for machining a rotor having a disc and a plurality of integral airfoils projecting outwardly from the disc, the method comprising a step of machining each airfoil with a disc tool having a grinding periphery thereof adapted for removing material from the airfoils, the grinding periphery having a thickness greater than a thickness of an adjacent supporting portion of the disc tool in order to permit the grinding periphery to pass a surface of an airfoil in a multi-axis simultaneous motion, thereby matching the grinding periphery with a predetermined geometry of a portion of the airfoil.
A method for machining a rotor having a disc and a plurality of integral airfoils projecting outwardly from the disc, the method comprising steps of:
- machining a portion of a surface of each airfoil with a conical disc tool in one pass, with respect to the surface;
- repeating the above machining step for other portions of the surface until completing machining of the entire surface;
- and
- wherein the conical disc tool has a grinding periphery at a wide end thereof adapted for removing material from the airfoil in a simultaneous motion of up to three translational and up to two angular degrees of freedom to allow machining of varying amounts of a curvature along the airfoil, thereby achieving a predetermined geometry of a portion of the airfoil in a single pass.
Dependencies are inferred from the claim text.