A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.
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.