COMBUSTOR LINER PANEL WITH A MULTIPLE OF HEAT TRANSFER RIBS FOR A GAS TURBINE ENGINE COMBUSTOR

摘要

A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.