designed to receive a combustion bowl in the axis of which an air and fuel injection device is mounted said flared bowl comprising downstream a divergent consisting of a double partition delimiting an annular cavity the first outer partition comprising inlet orifices arranged to cool the second inner partition by impact the second inner partition comprising outlet orifices a chamber characterized by the fact that the inlet orifices distributed in at least two circular rows on the periphery of the divergent are in staggered rows with the outlet orifices application_number US 33393008 A description fig2 shows the upstream end of a combustion chamber 1 for a turbojet comprising an air and fuel injection system 22 a fraction of the upstream air originating from the compressor is guided through the injection system 22 for the formation of a fuel air mixture injected along an axis x the latter enters the primary zone where the combustion reactions take place then the gases produced are diluted and cooled in the downstream secondary zone not shown and are distributed toward the turbine that they drive the injection system 22 comprises a fuel injector 2 with aerodynamic spraying for example as described in patent fr a 2 206 796 this injector 2 comprises a profiled central fuel delivery body extended downstream by swirling fins 23 with radial flow forming an internal centripetal spiral an annular cap 25 is provided with an inner channel connecting to the inner spiral 23 a row of outer fins 24 forming an outer spiral with substantially radial flow is.