A gas turbine blade may have a bond coat applied to its surface. The bond coat may include silicon and a reactive material. The reactive material may react with thermally grown oxide generated at the bond layer to prevent and reverse creep. One or more protective layers may be applied to 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.