COMBUSTOR WITH DILUTION HOLES

A combustor (16) of an aircraft engine comprises a liner (20) defining a primary and a dilution zone (32, 34) having a hot surface (26a, 26b) exposed to a flow of combustion gases traveling from the primary zone (32) downstream to the dilution zone (34) and a cold surface (26c, 26d). Dilution holes (36) extending through the liner (20) from the cold surface (26c, 26d) to the hot surface (26a, 26b) delimit the primary zone (32) from the dilution zone (34). Effusion holes (42) extending through the liner (20) from the cold surface (26c, 26d) to the hot surface (26a, 26b) direct cooling air (E) into the dilution zone (34). Two or more rows of effusion holes (42) positioned within three dilution hole diameters downstream of the dilution holes (36) are oriented relative to the liner (20) to direct the cooling air (E) in a cooling direction that is at least one of normal to the direction of the flow (D) of gases passing adjacent the effusion holes (42), and against the direction of the flow (D) of gases passing adjacent the effusion holes (42).