| 摘要 |
A combustion chamber ( 10 ) of a turbomachine, comprising at least one bowl ( 95 ) with a substantially frustoconical wall that is formed with an annular row of air injection orifices, and a fuel injector ( 36 ) arranged upstream of the bowl, the annular row of air injection orifices comprising smaller-diameter orifices ( 140 ) and larger-diameter orifices ( 142 ) which are arranged in alternating fashion and with a uniform distribution around the axis of the bowl to produce two annular air/fuel mixture layers ( 144, 148 ).
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