annular combustion chamber of a turbomachine and a turbomachine such as a turbojet or an airplane turboprop

摘要

A turbomachine combustion chamber including coaxial walls forming surfaces of revolution that include inlet orifices for admitting primary air and dilution air into the chamber, the orifices in each wall being substantially in alignment with one another along the longitudinal axis of the chamber and forming a single annular row of orifices.