A gas turbine blade having a surface may have a bond layer applied to a first section of the surface, wherein the bond layer is not applied to a second section of the surface. One or more protective layers may be applied such that the protective layers cover and overlap the bond layer making direct contact with an area of the surface immediately outside the first section of the surface and forming a mechanical constraint geometry about the edge of the bond layer.
STATEMENT OF FEDERALLY SPONSORED RESEARCH
 This invention was made with Government support under contract number DE-FC26-05NT42643 awarded by the Department Of Energy. The Government has certain rights in this invention.