US 11,788,727 B2
Injector nose for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit
Christophe Chabaille, Moissy-Cramayel (FR); Clément Yves Emile Bernard, Moissy-Cramayel (FR); and Sébastien Christophe Loval, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/417,505
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 26, 2019, PCT No. PCT/FR2019/053302
§ 371(c)(1), (2) Date Jun. 23, 2021,
PCT Pub. No. WO2020/136359, PCT Pub. Date Jul. 2, 2020.
Claims priority of application No. 1874261 (FR), filed on Dec. 27, 2018.
Prior Publication US 2022/0113024 A1, Apr. 14, 2022
Int. Cl. F23R 3/28 (2006.01)
CPC F23R 3/286 (2013.01) [F23R 3/283 (2013.01)] 11 Claims
OG exemplary drawing
 
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.