Patent ID: 8146364
Filing Date: 2012-04-03
Classification: F23R

Abstract:
1. A combustor for a gas turbine engine comprising: a combustor liner defining an interior combustion chamber having a flow-based longitudinal axis, the combustor liner comprising a plurality of circumferentially arranged arrays of apertures there through, each said array defined by a non-rectangular four-sided shape having an upstream edge, a downstream edge, and two lateral edges, each lateral edge, based on projection of the array onto a plane, intersecting with the upstream and downstream edges at an angle other than a right angle; a plurality of resonator boxes affixed to the liner, each said resonator box covering a respective array and having lateral walls conforming with the respective angles of the lateral edges, and each said resonator box comprising an upstream wall, a downstream wall, and lateral walls affixed to the liner; a downstream-TBC disposed along the inside surface of the combustor liner from a location downstream of the plurality of resonator boxes to a TBC first edge disposed upstream of the downstream wall, wherein no apertures through the liner pass through a portion of the downstream-TBC that is upstream of the downstream wall, and wherein impingement apertures through a top plate of the resonator box are provided over the portion of the downstream-TBC that is upstream of the downstream wall, wherein intervening strips of liner remain between adjacent resonator boxes; and wherein fluid flowing from the apertures within and adjacent the lateral wall upstream of a respective intervening strip is disposed to provide a film cooling to the intervening strip.