COMBUSTOR PANEL AND METHOD FOR COOLING THE SAME

A liner assembly for use in a combustor (56) of a gas turbine engine (20) is disclosed. In various embodiments, the liner assembly includes a panel (200; 300) defining a left side and a right side and a hot side (202) and a cold side, the panel having a dilution hole (206; 306) and a plurality of effusion holes (204; 304) extending between the hot side (202) and the cold side. In various embodiments, the plurality of effusion holes (204; 304) includes a first subgrouping (320) of effusion holes (204; 304) disposed downstream of the dilution hole (206; 306) and aligned in a generally left to right orientation toward a dividing line (318) extending downstream of the dilution hole (206; 306) and a second subgrouping (322) of effusion holes (204; 304) disposed downstream of the dilution hole (206; 306) and aligned in a generally right to left orientation toward the dividing line (318) extending downstream of the dilution hole (206; 306).