Slinger combustor

摘要

A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger.

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, the combustor shell having front and rear annular liners, 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, wherein the fuel atomization zone is provided in the form of a straight radially extending sub-chamber bounded by axially facing parallel inner peripheral ring portions of the front and rear annular liners, a plurality of nozzle air inlets defined in the fuel atomization zone of the combustor shell, the nozzle air inlets comprising at least one circumferential array of nozzle air inlets in each of the inner peripheral ring portions of the front and rear liners, each nozzle air inlet having a nozzle axis intersecting the stream of fuel centrifuged by the fuel slinger upstream of the radially outwardly flaring expansion zone, the nozzle axis having 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.