Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract: A structural connecting arm for an intermediate casing of an aircraft turbomachine with a ducted fan, wherein the arm is configured to connect a hub and an outer ferrule of the casing, and including an aerodynamic outer surface manufactured such that the arm also forms an outlet guide vane. Multiple metal ties extend in the longitudinal direction of the arm, together with a shell made from composite material surrounding the ties and forming the aerodynamic outer surface.