Injector nose for turbomachine including a secondary fuel swirler with changing section
An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis ( 44 ), and a secondary fuel circuit ( 64 ) comprising a secondary fuel swirler ( 114 ) formed of swirler channels ( 112 ) opening into a terminal fuel ejection portion ( 68 ) of annular shape arranged around the fuel ejection nozzle. Each swirler channel ( 112 ) has a passage section which decreases in a direction going from an upstream end ( 111 ) to a downstream end ( 115 ) of the swirler channel ( 112 ). The reduction of the passage section of the swirler channels ( 112 ) makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler ( 114 ) and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.
1. An injector nose for a turbomachine, including a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis, and a secondary fuel circuit comprising a secondary fuel swirler formed of swirler channels opening into a terminal fuel ejection portion of annular shape arranged around the fuel ejection nozzle, wherein each swirler channel has a passage section which decreases in a direction going from an upstream end to a downstream end of the swirler channel and wherein an entirety of each swirler channel extends along a respective plane forming, with the injection axis, a constant angle comprised between 40 degrees and 60 degrees.
2. The injector nose according to claim 1 , in which each swirler channel is curved in the respective plane.
3. The injector nose according to claim 1 , in which the secondary fuel circuit comprises a secondary plenum chamber of annular shape connected to the respective upstream ends of the swirler channels.
4. The injector nose according to claim 3 , in which the secondary fuel circuit comprises secondary connection channels connecting a tubular channel, centred along the injection axis, to the secondary plenum chamber.
5. The injector nose according to claim 1 , further comprising an air inlet swirler supplying an annular air injection channel arranged radially inwards with respect to the terminal fuel ejection portion and cooperating with the terminal fuel ejection portion to form a secondary aerodynamic injector.
6. The injector nose according to claim 5 , in which the terminal fuel ejection portion is delimited externally by an outer lip, and is delimited internally by an inner lip which separates the terminal fuel ejection portion from the annular air injection channel.
7. The injector nose according to claim 5 , in which the air inlet swirler is formed of air inlet channels having respective inlets opening through a radially outer wall of the injector nose, and respective outlets opening into the annular air injection channel.
8. An injection module for a turbomachine, comprising an injection system, and an injector nose according to claim 1 , in which the injection system comprises, from upstream to downstream, a bushing in which is mounted the injector nose, at least one air admission swirler emerging downstream of the injector nose, and a bowl.
9. Turbomachine, comprising at least one injector nose according to claim 1 .