CPC F23R 3/286 (2013.01) [F23R 3/283 (2013.01)] | 11 Claims |
1. Injector nose for a turbomachine, comprising:
a primary fuel circuit terminating in a fuel-ejection nozzle emerging on an injection axis, and
a secondary fuel circuit comprising an annular-shaped terminal fuel-ejection part arranged around the fuel-ejection nozzle,
wherein an upstream part of the primary fuel circuit, housed in the injector nose, comprises an annular channel extending around the secondary fuel circuit and delimited by an external wall of the injector nose,
wherein the injector nose further comprises air inlet channels extending through the annular channel of the primary fuel circuit and having respective inlets opening in the external wall and respective outlets emerging in an annular air-injection channel arranged radially to the inside with respect to the terminal fuel-ejection part, around the fuel-ejection nozzle, and cooperating with the terminal fuel-ejection part in order to form an aerodynamic secondary injector.
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