ARRANGEMENT FOR LASER PROCESSING OF TURBINE COMPONENT

摘要

An arrangement (10) for laser deposition repair of a gas turbine engine component (20). A processing surface (52) of the component is precisely positioned relative to a laser material deposition device (12), while service induced distortions of the component are accommodated by adjustment of a moveable base (28) remote from the processing surface, thereby allowing a plurality of like-design components to be processed without the necessity for part-specific dimensional verification or reprogramming of the device.

主权项

1. An arrangement for laser processing of a gas turbine engine blade, the arrangement comprising:
a frame; a first split plate removeably supported by the frame and defining an opening for receiving a tip of the blade when the plate is assembled on the frame, the first split plate comprising a powder support surface surrounding the opening; and a positionable base for supporting the blade such that a top surface of the tip aligns with the powder support surface in a processing plane when the blade is supported on the base; wherein the first split plate opening is effective to locate the blade tip at a predetermined position relative to the frame for a laser material deposition process independent of dimensional deviations in the blade below the tip.