Patent ID: 9335049
Filing Date: 2016-05-10
CPC Classification: F23R

Claim Text:
1. A combustor liner for a gas turbine engine, the combustor liner being arcuate in shape and defining an axis and a circumferential direction, the combustor liner comprising: a first row of dilution openings in the liner, the first row of dilution openings running in the circumferential direction; and a second row of dilution openings in the liner, the second row of dilution openings running parallel to the first row of dilution openings and axially spaced from the first row of dilution openings; each dilution opening of the second row of dilution openings at least partially overlapping in an axial direction a portion of each of two adjacent dilution openings of the first row of dilution openings; and wherein the dilution openings are substantially rectangular.