Fuel injector with a purge circuit for an aircraft turbine engine
AssigneeSafran Helicopter Engines
InventorsThomas Jean Olivier Lederlin, Denis Luc Alain Chanteloup, Simon Arthur Meilleurat
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Abstract
A fuel injector for an aircraft turbine engine includes a tubular body having an axis of elongation. A first longitudinal end configured to be Supplied with fuel and a second longitudinal end configured to elect a jet of fuel. The body further includes an integrated purge-air circuit that has an internal cavity which is connected to air inlet orifices situated on the body and to at least one air outlet situated at said second end. Aire-flow disruptors are provided, projecting into said cavity.
Claims13
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 second end comprises a elongated tubular portion comprising an axis of elongation substantially perpendicular to said axis of elongation of said body, said elongated tubular portion having two longitudinal ends which are opened and which are configured to form respectively two inlets distinct for two fuel flows intended to meet together at the middle of said elongated tubular portion, said elongated tubular portion comprising at least one slot for ejecting a flat jet of fuel.
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.
Dependencies are inferred from the claim text.