Patent ID: 7673456

Claim:
A turbomachine combustion chamber comprising: an inner annular wall about a longitudinal axis; an outer annular wall centered on the longitudinal axis and surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area; and a plurality of fuel injector systems comprising pilot injectors alternating circumferentially with full-throttle injectors; the combustion chamber further comprising at least one air admission opening opening out into the upstream end of the combustion area in a direction that is substantially longitudinal; wherein the outer wall includes a plurality of pilot cavities that are regularly distributed around the longitudinal axis, each pilot cavity extending longitudinally between the two longitudinal ends of the outer wall and radially towards the outside thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction; and wherein each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between said adjacent pilot cavities.