Patent ID: 7036316

Claim:
A method for assembling a combustor for a gas turbine engine, said method comprising: coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween; positioning an outer support a distance radially outward from the outer liner; positioning an inner support a distance radially inward from the inner liner; forming at least two rows of impingement openings extending through at least one of the inner support and the outer support for channeling impingement cooling air therethrough towards at least one of the inner liner and the outer liner; and forming at least one row of dilution openings extending through at least one of the inner liner and the outer liner for channeling dilution cooling air therethrough into the combustion chamber, such that a pressure differential across the at least two rows of impingement openings is substantially equal to a pressure differential across the at least one row of dilution openings.