| 摘要 |
A fuel injection device 110 for a turbine engine comprises a pilot injector 122 opening out into a venturi 120 and an annular row of multipoint injection orifices 136 opening out axially in a downstream direction and radially outside the venturi. The venturi is connected at its downstream end to a separation wall 140, the separation wall having an outer peripheral edge 142 with a diameter (fig 3, B) greater than that of the annular row (fig 3, A) of injection orifices. The separation wall thus forms a thermal protection screen for the orifices against heat radiation from the chamber. The venturi may have an inner cavity 160 fed with air and include two sets of orifices 162, 163 to allow the passage of air through the venturi from the outside of the venturi to the inside. |
