| 主权项 |
1. A slinger combustor for a gas turbine engine, the slinger combustor comprising: an annular combustor shell concentrically disposed about a central axis and defining an annular combustion chamber having a radially inner annular fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger mounted for rotation about the central axis, a fuel atomization zone extending radially outwardly from the radially inner circumferential fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone, a plurality of nozzle air inlets defined in the fuel atomization zone of the combustor shell, the nozzle air inlets having a nozzle axis intersecting the stream of fuel centrifuged by the fuel slinger and a tangential component in a direction of rotation of the fuel slinger, and a plurality of dilution holes defined in the combustor shell, the dilution holes having a dilution axis intersecting the combustion zone, and wherein the dilution axis of at least some of the dilution holes has a tangential component in a circumferential direction opposite to the direction of rotation of the fuel slinger. |
