Patent ID: 7900457
Filing Date: 2011-03-08
Classification: F23R,Y02T

Abstract:
1. A method for fabricating a combustor liner for a gas turbine engine, 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 secondary dilution holes in the second panel, wherein the plurality of primary dilution holes and the plurality of secondary dilution holes are configured to discharge dilution air into the shell; and forming a plurality of circumferentially aligned cooling holes in at least one of the first panel and the second panel, wherein the plurality of circumferentially aligned cooling holes includes a first group of cooling holes having a first size, a second group of cooling holes having a second size different than the first size, and a third group of cooling holes having a third size different than the first size and the second size.