| 摘要 |
<p>A thermal barrier coating for superalloy turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes a ceramic layer applied to an Aluminide or MCrAlY bond coat (12) by electron beam physical vapor deposition. The ceramic layer has a first portion (26) having unstabilized porosity, a second portion (28) overlying the first portion, with stabilized porosity, and an outer portion (30) wherein the pores are coated with a noble metal. The stabilized porosity portion along with the noble metal coating reduce the thermal conductivity of the ceramic layer. Stabilizing the porosity renders it more resistant to sintering densification at high temperatures.</p> |
