Fuel injection system for annular combustion chamber of e.g. turbojet of aircraft, has swirler including blades defining channels, where trailing edges of blades extend on widened truncated surface around longitudinal axis

摘要

The system has a support unit (140) for supporting and centering a head (130) of a fuel injector. A truncated mixing bowl (142) is arranged downstream of the support unit. A radial swirler (134) is located between the support unit and the bowl. The swirler includes blades (180) defining radial channels for passage of air flow. The channels are contained within a radial plane. Trailing edges (178) of the blades extend on a widened truncated surface around a longitudinal axis of the system. The swirler includes a cylindrical peripheral edge (189) fixed on a venturi nozzle (138).