Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Jacques A Roche

Xavier J Pasquali

Olivier M Mahias

Mireille S Romero

Elisabeth Vilfeu

An afterburner for a turbofan engine is disclosed having a plurality of connecting arms connecting the inner wall to the outer wall wherein each of the connecting arms defines an air chamber, an inlet communicating with the main air bypass passageway and a plurality of outlets communicating with the afterburner chamber. The plurality of connecting arms are distributed generally radially about the longitudinal axis of the engine and serve to distribute a portion of the bypass air into the afterburner chamber. The bypass air is further distributed into the afterburner chamber through a plurality of flame holders extending radially inwardly from the outer wall towards the longitudinal axis. Each of the flame holders also defines an air chamber, an inlet communicating with the main air bypass passageway and a plurality of air outlets. The flame holders may also be distributed in a radial array about the longitudinal axis and are interposed between adjacent connecting arms.

Afterburner for a turbofan engine

A fuel injector for a turbojet engine afterburner is disclosed having a fuel tube extending radially inwardly into an afterburner combustion chamber from the engine casing, the fuel injector tube defining a plurality of downstream facing fuel discharge orifices along a portion of its length in order to discharge fuel into the afterburner combustion chamber. A cooling device is associated with the fuel tube in order to direct cooling air from a bypass passage of the engine onto the fuel tube in order to cool the fuel tube, not only when the afterburner is in operation, but also when the afterburner is not in operation. The cooling device is an elongated tubular enclosure which substantially encloses the fuel tube, the elongated tubular enclosure having a significantly larger cross-sectional area than that of the fuel tube so as to define a cooling cavity between them. The elongated tubular enclosure, which is also attached to the turbojet engine casing, passes through the bypass passage and defines inlet openings to enable a portion of the air in the bypass passage to pass through the opening and into the cooling cavity so as to cool the fuel tube. A downstream portion of the elongated tubular enclosure defines a slit which is in alignment with the plurality of fuel discharge orifices of the fuel tube so as to enable the fuel to be injected into the afterburner combustion chamber.

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Lisses, France

Jacques A Roche