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: An annular wall for the combustion chamber of a turbomachine has a cold side and a hot side, said wall being provided with a plurality of primary holes and a plurality of dilution holes distributed in circumferential rows, together with a plurality of cooling orifices that are distributed in a plurality of circumferential rows that are spaced apart axially from one another, the number of cooling orifices being identical in each row thereof, and the wall further including bores disposed immediately downstream from the primary holes and from the dilution holes and distributed in circumferential rows, the bores in any one row presenting a substantially identical diameter, being spaced apart at a pitch that is constant, and presenting intrinsic characteristics that are different from the intrinsic characteristics of the cooling orifices of the adjacent rows.

Abstract: A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

Abstract: A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

Abstract: A diffuser for a single-head annular combustion chamber of an airplane engine, the diffuser comprising a separator formed by a thin sheet connected by structural arms to inner and outer circularly-symmetrical walls of the diffuser, the diffuser angle for each diffusion stream defined by the separator lying in the range about 12° to about 13°.

Abstract: The invention concerns a double flow turbo-jet engine, including a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manihold and a protective tubular screen of the manihold. The invention is characterised in that the gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manihold.

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.