Air-fuel mixture injection device for combustion chamber of aircraft turbojet, has air injection orifices arranged in extension of blades in direction of flow of air along blades when viewed along axial direction

摘要

The device has a fuel injector support including a sleeve for receiving a fuel injector, and an annular flange extending radially outward of the sleeve. An annular air injection swirler has stationary blades (60) to inject a swirling flow of air. The support has air injection holes distributed circumferentially about an axis (X-X) of the device and opened in the interior of the device via air injection orifices (58). Each orifice is arranged in the extension of the blades in a direction of the flow of air along the blades, when viewed along an axial direction defined by the axis of the device.