EFFUSION COOLING FOR GAS TURBINE COMBUSTORS

摘要

A combustor for a turbine engine includes an outer liner and an inner line r circumscribed by the outer liner to form a combustion chamber therewith in which an air and fuel mixture is combusted to form streamlines of combustion gases. A fir st plurality of effusion cooling holes is formed in at least one of the inner or outer liner s, with the first plurality of effusion cooling holes being oriented as a function of the streamlines.