Patent ID: 8739546

Claim:
An annular combustor for a gas turbine engine, comprising: a first annular liner extending along a longitudinal axis; a second annular liner spaced radially outboard of and generally coaxially circumscribing the first liner, each of the first annular liner and the second annular liner having a heat shield mounted to a shell; a bulkhead extending between a forward end of the first liner and a forward end of the second liner and cooperating therewith to define a combustion chamber for combusting fuel in air; a plurality of first dilution air admission holes formed in the first annular liner and arranged in a circumferential row at circumferentially spaced intervals; a plurality of first dilution air admission holes formed in the second annular liner and arranged in a circumferential row at circumferentially spaced intervals; and a plurality of quench air admission holes formed in at least one of the first and the second annular liners, said plurality of quench air admission holes being arranged in a circumferential row disposed downstream of the plurality of first dilution air holes and offset circumferentially from the plurality of dilution air holes disposed upstream thereof, each of said plurality of quench air admission holes including a respective hole in the shell and a corresponding hole in the heat shield of said at least one of the first and the second annular liners.