Patent ID: 11933497
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An air and fuel injection system of a turbomachine comprising:
an injector comprising a pipe and an injection nose housed inside the pipe, the pipe extending from upstream to downstream along a longitudinal axis;
a mixing device comprising a bowl, the bowl comprising an annular inlet, forming an inlet of the mixing device, from which a conical portion flared downstream extends, the mixing device being disposed downstream of the injection nose;
wherein the injector comprises an air injection ring extending from the pipe and from which a connection bushing comprising a divergent portion extends, the connection bushing being disposed externally around the annular inlet of the mixing device, wherein the inlet of the mixing device comprises an outer surface, the injector connection bushing being in contact with the inlet of the mixing device via the outer surface and the injector connection bushing being rotatably mounted in the mixing device.