TUNGSTEN CARBIDE INSERTS FOR A GAS TURBINE LINER AND METHOD

摘要

Systems and methods provide for wear reduction in a combustion system of a gas turbine. A system for wear reduction includes: at least one substantially H-shaped block ( 202 ), the substantially H-shaped block ( 202 ) being configured to secure a transition piece ( 10 ) of a gas turbine combustor to a support piece; a first insert including a tungsten carbide in a metal matrix, the metal matrix being selected from a group including cobalt and nickel; and a brazing material which is used in brazing the first insert to the at least one substantially H - shaped block ( 202 ) in at least one location on an interior wear surface of the at least one substantially H-shaped block ( 202 ).