| 摘要 |
PROBLEM TO BE SOLVED: To provide a coating for preventing corrosion of components of a turbine engine subjected to elevated operating temperature. SOLUTION: A corrosion resistant coating is constituted for the components of the engine such as turbine disks, turbine seal elements and turbine shafts. This coating may also find application within a gas fluid flow path or to the other turbine components including turbine vanes, turbine stator vanes, liners and exhaust flaps. This corrosion resistant coating used for a gas turbine component includes a glassy ceramic matrix. The glassy matrix is a silica base, and particles are selected from a group of MCrAlX particles being refractory oxide particles substantially uniformly distributed in the matrix and a combination of these particles. Refractory oxide and/or MCrAlX constitute an corrosion resistant coating. COPYRIGHT: (C)2007,JPO&INPIT
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