Fuel injecting system for annular combustion chamber of turbo machine e.g. jet engine, of aircraft, has spin whose upstream end comprises annular upstream cowl guiding air toward outside with respect to axis of spin

摘要

The system (126) has a support unit supporting a head of a fuel injector. A radial spin (144) produces a flow of air radially turning in a downstream of the head of the injector. An upstream end (148) of the spin comprises, with external periphery, an annular upstream cowl (160) guiding the air toward outside with respect to an axis of the spin, where the upstream end of the spin comprises, at an internal periphery, an internal cylindrical surface centering the head of the injector, and an annular internal throat traversed axially by the head of the injector. An independent claim is also included for an annular combustion chamber of a turbo machine.