Process and system for forming shaped air holes
A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
1. A method for forming shaped holes, comprising:
forming a plurality of shaped portions of air holes in a turbine component using a first short-pulse laser;
after forming the plurality of shaped portions, then forming a plurality of metered holes through the turbine component extending from the shaped portions of the air holes to an inner cavity of the turbine component, wherein each metered hole corresponds to one of the plurality of shaped portions of air holes; and
after forming the plurality of metered holes, then finishing the air holes by smoothing, applying surface textures, and/or applying surface contours to the respective shaped portions.
2. The method of claim 1 , wherein finishing the air holes comprises removing cracks.
3. The method of claim 1 , further comprising a three dimensional-laser scanner for controlling the first short-pulse laser based on a CAD file provided to the three dimensional-laser scanner.
4. The method of claim 1 , wherein first short-pulse laser has a pulse duration less than 10 μs.
5. The method of claim 1 , wherein the metered hole is formed using a long-pulse laser, a water jet, an electrical discharge machining system, an electron beam machining or an electrochemical machining system.
6. The method of claim 5 , wherein the long-pulse laser has a pulse duration ranging from 1 μs to 1 ms.
7. The method of claim 5 , wherein the long-pulse laser has a power rating greater than 50 W.
8. The method of claim 1 , wherein forming the plurality of shaped portions comprises forming the plurality of shaped portions in at least a thermal barrier coating layer of the turbine component.
9. The method of claim 1 , comprising:
validating one or more of the shaped portions, the metered holes, or the finished air holes based upon a volumetric reconstruction and a CAD file.
10. The method of claim 1 , comprising assessing the finished surface of the shaped portions using one or more of IR imaging, confocal microscopy, or X-ray radiography.
11. The method of claim 1 , wherein finishing the air holes comprising using a second short-pulse laser operated at a different scan rate than the first short-pulse laser.