AIRCRAFT TURBOMACHINE COMBUSTION CHAMBER MODULE AND METHOD FOR DESIGNING SAME

摘要

Combustion chamber module for aircraft turbomachine comprising an annular combustion chamber in which each of the primary (62e) and dilution (64e) orifices in the outer annular wall (14) which is located at least partially in the wake (54) of a fuel injector (22) has a coefficient of discharge higher than that of its counterpart in the inner annular wall. Method of designing such a module involving determining the wakes (54) generated by the injectors (22) defining the geometry of the air inlet orifices (44e 46e) in the coaxial walls of the combustion chamber so that the airflow actually entering via the orifices (44e 46e) in the outer wall (14) is substantially equal to the flow of air entering via the orifices in the inner wall.