Patent ID: 11892166
Assignee: SAFRAN HELICOPTER ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 11:
12. A fuel injector for an aircraft turbine engine, comprising a tubular body having an axis of elongation and comprising a first longitudinal end configured to supply fuel and a second longitudinal end configured to eject a jet of fuel, said body further comprising an integrated purge air circuit which comprises an internal cavity in fluid communication with air supply orifices located on the body and which comprises an annular portion extending around said axis of elongation and connected to air outlet channels opening at said second end, wherein air flow disruptors are provided projecting into the annular portion of said internal cavity,
wherein said cavity comprises two channels diametrically opposed with respect to said axis of elongation and each defining an air outlet at said second end, each of the channels comprising projecting disruptors,
wherein the disruptors of each of the channels comprise several partitions,
and wherein the partitions are parallel to each other and parallel to said axis of elongation.