Patent ID: 7895841

Claim:
A method for fabricating a combustor liner for a gas turbine engine, said combustor liner extending from a forward end to and aft end along a centerline of the combustor liner, said method comprising: providing an annular shell including a plurality of circumferentially extending panels that overlap adjacent ones of the plurality of panels in an axial direction, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel; forming a plurality of primary dilution holes in the first panel; forming a plurality of evenly spaced secondary dilution holes in the second panel, the secondary dilution holes circumferentially offset from the primary dilution holes such that the primary dilution holes and the secondary dilution holes are configured to discharge dilution air into the shell; positioning the secondary dilution holes a distance from the primary dilution holes, wherein the distance is whitin a range of twice a diameter of the secondary dilution holes to four times the diameter of the secondary dilution holes.