INDUSTRIAL TURBINE NOZZLE BLADE-FORM PART, TOP COATING SYSTEM FOR OTHER HOT GAS PASSAGE CONSTITUENT PART, AND METHOD RELATED TO THE TOP COATING SYSTEM

摘要

PROBLEM TO BE SOLVED: To provide a turbine constituent part 50 having a heat insulating coating film 62 on at least one of its surface parts and used in a hot gas passage of a gas turbine. SOLUTION: The turbine constituent part includes a protective top coating 64 with a predetermined thickness and having alumina particles in a silica-containing matrix. The alumina particles constitute approximately 5-85 wt.% of the outer protective top coating, and the silica-containing matrix contains silica, silicate, and mullite and constitutes approximately 1-45 wt.% of the outer protective top coating. The thickness is decided as a function of the temperature of the heat insulating coating film in service. COPYRIGHT: (C)2005,JPO&NCIPI