System for cooling the wall of a gas turbine combustor.

摘要

In one embodiment, a system includes an engine panel (58). The engine wall (58) has a cold side (72) and a hot side (74). The engine wall (58) is formed with one or more dilution holes (70), wherein each of the dilution holes (70) includes: a first orifice on the cold side (72), a second orifice on a hot side (74), and a portion of a A thermal barrier coating (TBC) (78) mounted on the cold side (72) and having an opening substantially surrounding the first orifice.