Safran Helicopter Engines

Thomas Jean Olivier Lederlin

Simon Arthur Meilleurat

Guillaume Gerard Joel Mauries

Christophe Laurent

Denis Luc Alain Chanteloup

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.

Fuel injector with a purge circuit for an aircraft turbine engine

A pre-vaporisation tube for a turbine engine combustion chamber includes a main body ROOM defining a first inner duct configured to have an injector mounted therein. The tube includes a first end attached to a wall of the chamber, and at least two end pieces are arranged at a second end of the body and define second inner ducts. The end pieces include first portions and second portions, respectively. The second portions each include two coaxial cylindrical walls which are inner and outer coaxial cylindrical walls, respectively, and which define an annular cavity therebetween. The inner wall defines an inner passage and has first openings for fluid communication between the passage and the annular cavity.

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Moissy-Cramayel, France

Thomas Jean Olivier Lederlin