HYBRID THROUGH HOLES AND ANGLED HOLES FOR COMBUSTOR GROMMET COOLING

摘要

Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner 200 of an aircraft, comprising: a plurality of angled holes 208, and at least one through hole 206 separating all combinations of any two of the angled holes 208, wherein the at least one through hole 206 is oriented at an angle that is substantially perpendicular to a surface of the liner 200, and wherein each of the plurality of angled holes 208 are non-parallel to the at least one through hole 206.