Component i.e. moving blade, for environment of hot gas path of e.g. aircraft gas turbine utilized for sucking and compressing air, has internal channel for supplying protective gas near to layer/layer system or inside of layer/layer system

摘要

#CMT# #/CMT# The component i.e. moving blade (RB), has a base component with a portion that is partially made of fiber-matrix composite material, which is inflammable under operating temperature of a hot gas environment. A surface of the base component is provided with a protecting layer (LA) or layer system. An internal channel is provided in the base component for supplying protective gas (PROG) near to the layer/layer system or to an inner side of the layer/layer system. The material is selected from a group consisting of carbon, silicon carbide, boron nitride, silicon nitride and aluminum carbide. #CMT# : #/CMT# The protective gas is selected from inert gas and active gas. Independent claims are also included for the following: (1) a method for manufacturing a gas turbine component (2) a method for operating a gas turbine. #CMT#USE : #/CMT# Component i.e. moving blade (claimed), for an environment of a hot gas path of a gas turbine e.g. stationary gas turbine and aircraft gas turbine, which is utilized for sucking and compressing air in a compressor part at combustion chamber pressure for combustion of gaseous or liquid fuel to convert flow energy into mechanical energy. #CMT#ADVANTAGE : #/CMT# The internal channel is provided in the base component for supplying the protective gas near to the protecting layer/layer system or to inner side the layer/layer system, so that the gas turbine component can tolerate high temperatures, thus prolonging service life of the gas turbine component. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a schematic longitudinal sectional view of a gas path of a gas turbine. GT : Gas turbine HGP : Hot gas path LA : Protecting layer PROG : Protective gas RB : Moving blade.