| 摘要 |
A fuel injection device (110) for a turbine engine, the device comprising a pilot injector 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 being connected at its downstream end to a separation wall (140), the device being characterized in that the outer peripheral edge (142) of the separation wall has a diameter (B′) greater than the diameter of the annular row (A) of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber. |
