| 摘要 |
An airblast fuel injector (200) for a fuel spray nozzle of a gas turbine engine is provided. The injector has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage (202), an annular fuel passage (204), an annular outer air swirler passage (206), and an annular shroud air swirler passage (208). The injector further has an annular shroud (211) having an inner surface profile (212) which defines a radially outer side of the shroud air passage. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section (214) followed by a divergent section (216), the transition from the convergent section to the divergent section forming a first inwardly directed annular nose (N1). The injector further has an annular wall (218) having an outer surface profile (220) which defines a radially inner side of the shroud air passage, and having an inner surface profile (222) which defines a radially outer side of the outer passage. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section (230) followed by an outwardly turning section (232) which faces across the shroud air passage to the first nose (N1). |
