| 摘要 |
PROBLEM TO BE SOLVED: To provide a method for repairing a covered high pressure turbine blade exposed to operation of an engine so as to restore the covered impeller part appearance dimension of the blade. SOLUTION: A heat insulation film system includes an upper layer ceramic heat insulation film containing a diffused bonding coat on a base metal substrate and yttria stabilization zirconia material. The upper layer ceramic heat insulation film has nominal thickness t. Further, it includes a stage for removing the heat insulation film system so as to remove a part of the base metal substrate and measuring the thickness of the removed base metal substrate. One part of the removed base metal substrate has thicknessΔt. Further, it includes a stage for re-enforcing a diffused bonding coat on the substrate so as to re-enforce to the same thickness as the thickness enforced prior to operation of the engine; and a stage for re-enforcing the upper layer ceramic heat insulation film to the nominal thickness +Δt so as to compensate the part of the base metal substrate removed byΔt. COPYRIGHT: (C)2005,JPO&NCIPI |
