| CPC B29C 73/26 (2013.01) [B23B 35/00 (2013.01); G05B 19/402 (2013.01); F01D 25/005 (2013.01); F01D 25/24 (2013.01)] | 5 Claims |
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1. A method of repairing a combustor liner of a gas turbine engine, the method comprising:
removing an existing coating material from the combustor liner;
acquiring first measured data indicative of a geometry of a region of the combustor liner including a first hole and a second hole with the combustor liner in an uncoated state;
using the first measured data, determining:
a first location and a first orientation of the first hole in the combustor liner with the combustor liner in the uncoated state; and
a first location and a first orientation of the second hole in the combustor liner with the combustor liner in the uncoated state;
applying a new coating material on the combustor liner so that the first hole is substantially unobstructed by the new coating material and the second hole is at least partially obstructed by the new coating material, an application of the new coating causing deformation of the combustor liner;
acquiring second measured data indicative of a geometry of the region of the combustor liner where the region of the combustor liner is in a coated state;
using the second measured data, determining a second location of the first hole with the combustor liner in the coated state;
inferring a second location of the second hole with the combustor liner in the coated state using:
the second location of the first hole; and
a spacing between the first location of the first hole and the first location of the second hole;
determining a second orientation of the second hole with the combustor liner in the coated state based on the first orientation of the second hole; and
drilling through the coating material at least partially obstructing the second hole using the second location and the second orientation of the second hole.
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