INJECTOR OF A MIXTURE OF AIR AND FUEL FOR A TURBOMACHINE COMBUSTION CHAMBER

摘要

Injector (12 ') of an air and fuel mixture for a combustion chamber (10) of a turbomachine, in particular of an aircraft, comprising a body (14) comprising or defining at least one fuel circuit ( 16) and at least one air circuit (18), the injector further comprising a dome (20 ') located at one end of said body and configured to define a chamber (22) for premixing the air and the fuel leaving said circuits, the dome comprising an opening (24 ') for projecting an air-fuel cone, characterized in that this opening has a peripheral edge (26') having notches (30 '). Figure for the abstract: Figure 3