Method for improved deburring of an aeronautical part
A method for deburring an aeronautical part with an articulated tooling including a plurality of axes of rotation, the aeronautical part including at least one edge to be deburred, the articulated tooling including a tool holder, holding a calibration tool and a machining tool, the calibration tool and the machining tool being fixed to the tool holder and being immovable relative to one another, the method including steps of calibrating the calibration tool and the machining tool, of parameterizing the aeronautical part, of deburring the at least one edge to be deburred with the machining tool moving along a predetermined trajectory, on the basis of the parameters obtained during the parameterization step.
1. A method for deburring a turbomachine disk comprising a plurality of slots with an articulated tooling, the articulated tooling comprising a plurality of axes of rotation, the turbomachine disk comprising at least one edge to be deburred, the at least one edge to be deburred being a bottom edge of a slot of the plurality of slots of the disk, the articulated tooling comprising a tool holder, the tool holder holding a calibration tool and a machining tool, the calibration tool and the machining tool being attached to the tool holder and being immovable relative to one another, the method comprising steps of:
calibrating the calibration tool and the machining tool to determine the relative position of the calibration tool relative to the machining tool,
parameterizing the turbomachine disk via the calibration tool, to determine the position of the turbomachine disk relative to the articulated tooling,
deburring the at least one edge of the bottom of the slot to be deburred with the machining tool moving along a predetermined trajectory, on the basis of the parameters obtained during the parameterizing.
2. The method according to claim 1 , wherein the at least one edge to be deburred comprises a plurality of edges to be deburred uniformly distributed around a central axis of the turbomachine disk.
3. The method according to claim 1 , wherein the predetermined trajectory is a circular arc.
4. The method according to claim 1 , wherein the calibration step is carried out via successive contacts between at least one calibration ball and the calibration tool, and between the at least one calibration ball and the machining tool.
5. The method according to claim 1 , comprising, between the parameterizing and the deburring, a step of defining, via the calibration tool, a first reference point on a first edge of the at least one edge to be deburred, and on the basis of parameters determined at the parameterizing, said first reference point being a starting point of the predetermined trajectory during the deburring.
6. The method according to claim 5 , wherein, after deburring the first edge to be deburred, a second reference point is determined, via circumferential projection of the first reference point, on a second edge of the at least one edge to be deburred, and wherein according too the parameters determined in the parameterizing, then the second edge to be deburred is deburred starting from the second reference point and along the predetermined trajectory.
7. The method of claim 6 , wherein the deburring and projection steps of reference points are repeated over at least a portion of the circumference of the turbomachine disk.
8. The method according to claim 1 , wherein the articulated tooling is a robot with six axes of rotation, and wherein a single axis among the six axes is used during the deburring, the other axes being substantially fixed.
9. The method according to claim 8 , wherein said single axis is oriented parallel to a central axis of the turbomachine disk during the deburring.
10. The method according to claim 1 , wherein the machining tool is a hemispherical tip milling tool, and the calibration tool is a touch probe.