Abstract: A device for feeding air and fuel to a burner ring in an after-burner chamber, including a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, and a burner ring made up of ring sectors mounted substantially end to end on the flame-holder arms, the ring sectors containing fuel feed rail and air manifold boxes.

Abstract: Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between two circumferentially-directed parallel plates (34, 36) of the flameholder arms (14) and are immobilized between these plates (34, 36) by locking pieces (52) which are themselves held between the plates (34, 36) by immobilizing means (54, 56) engaged in aligned orifices (58, 60, 64) in the plates (34, 36) and in the locking pieces (52).

Abstract: The invention relates to a burner ring for turbofan jet engines. The ring includes an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold for injecting fuel into the channel. The ring includes multiple sectors connected together. Each sector has a fuel inlet which is connected to the fuel injection manifold. Part of the upstream annular envelope is in the core flow. Each sector has a connector which receives the fuel inlet and a ventilation duct which extends through the channel and upstream of the injection manifold. Each sector is fitted with an inlet for a bypass air, which air is then emitted by the ventilation duct to cool the injection manifold. A sector of downstream annular envelope is arranged downstream of the injection manifold to protect this manifold.

Abstract: Flameholder arm for an afterburner of a turbomachine, particularly a jet engine, comprising a ventilation duct (24) which is centered and immobilized inside the arm (10) by means independent of the heatshield (28), the duct also comprising a transverse lip (50) comprising an orifice (56) for centering and guiding a fuel injection harness (26) preventing this harness from being positioned in any way incorrectly in the arm (10).

Abstract: A device for fastening a fluid duct such as a fuel duct in an orifice of a turbojet casing, the device comprising a ring screwed into the orifice of the casing and having an annular rim coming to bear against a washer at the end of the duct, and a nut screwed onto the end of the duct so as to clamp the annular rim of the ring against the washer of the duct in order to fasten the duct to the casing.

Abstract: The turbojet of the invention includes a combustion chamber, a channel for heating the gas stream, where the heating channel includes at least one device for injection of fuel into the gas stream, which includes an open chamber, with a U-shaped section, having at least one wall within which extend fuel-injection means, which inject the fuel in at least one direction. It is characterised by the fact that a cooling jacket is provided in the chamber, alongside the wall forming the base of its U-section, and the fuel injection device includes protection means interposed between the fuel-injection means and the wall, in a fuel-injection direction. Thus, as a result of the invention, the fuel injection device, which is bathed in a very hot environment, is protected against thermal shocks due to the projection of colder fuel onto its walls, and its life expectancy is therefore increased.

Abstract: A device for feeding air and fuel to a burner ring in an after-burner chamber comprises a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, a burner ring made up of ring sectors mounted substantially end to end on the flame-holder arms, and means for feeding air and fuel to the burner ring sectors, said means extending between the burner ring and the outer casing of the after-burner chamber inside the flame-holder arms.

Abstract: Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between two circumferentially-directed parallel plates (34, 36) of the flameholder arms (14) and are immobilized between these plates (34, 36) by locking pieces (52) which are themselves held between the plates (34, 36) by immobilizing means (54, 56) engaged in aligned orifices (58, 60, 64) in the plates (34, 36) and in the locking pieces (52).

Abstract: The invention relates to an afterburner ring 19 for turbofan jet engines. The ring comprises an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold 4 for injecting fuel into the channel. The ring has sectors 20 which each comprise a sector 1 of the upstream annular envelope. Each sector 1 has a fuel inlet 35 which is connected to the injection manifold 4. Part of the upstream annular envelope is in the core flow. Each sector 20 has a connecting means which receives the fuel inlet and a ventilation duct 2 which extends through the channel along the sector 1, at a point upstream of the injection manifold 4. Each sector 1 is fitted with an inlet for bypass air, which air is then emitted by the ventilation duct 2 to cool the injection manifold 4. A sector 5 of downstream annular envelope is arranged downstream of the injection manifold 4 to protect it.

Abstract: Printer for printing machine comprising a plurality of styluses arranged in a plane parallel to the writing line and a corresponding number of electromagnets whose armatures cooperate with one end of the styluses mounted in a fixed guide, the other end being driven by a movable guide, characterized by means for subjecting the guide to a first alternating linear movement parallel to the writing line combined with a second alternating linear movement perpendicular to the first one, the amplitude of these linear movements corresponding to an integral number of characters printed in the form of dot matrixes.The invention can be applied to high speed printers operating at 300 to 500 lines per minute.