Patent ID: 9347667
Filing Date: 2016-05-24
CPC Classification: F23D,F23R

Claim Text:
1. A dual fuel circuit injector for a gas turbine combustion chamber, comprising: fuel supply circuits including a starting fuel supply circuit configured to supply fuel during chamber ignition, and to operate in any flight mode, and a main fuel supply circuit configured to operate in any flight mode subsequent to starting, and an air circuit, wherein the starting fuel supply circuit and the main fuel supply circuit include parallel conduits made in a common tube with a longitudinal axis, wherein the conduit of the starting fuel supply circuit opens, on one end, substantially into a center of a spherical injector body at a downstream end of the common tube, with respect to fuel flow through the common tube, and, on the one end, the conduit of the starting fuel supply circuit houses an injection ring configured to drive fuel into rotation before projecting the fuel inside the gas turbine combustion chamber through a central channel passing through a central wall of a swirling device, wherein the conduit of the main fuel supply circuit opens into an annular channel made in the spherical injector body facing jet channels radially configured in the central wall of the swirling device around the central channel, the annular channel being C-shaped to include two separated channel ends and being fixed to an upstream face of the central wall of the swirling device, with respect to fuel flow, and wherein air in the air circuit is guided in a passage delimited between the spherical injector body and a spherical portion of a sheath surrounding the spherical injector body, the sheath including an opening into which the swirling device opens, wherein a plane defined by a downstream face of the central wall of the swirling device, with respect to fuel flow, is offset from the opening of the sheath along an axis of the swirling device.