A fuel injector and a gas turbine engine combustion chamber

摘要

A gas turbine engine lean burn fuel injector (44) comprises a fuel injector head (48) which has a first air swirler (61), a second air swirler (73) arranged around the first air swirler (61), a pilot fuel injector (66, 68) arranged radially between the first air swirler (61) and the second air swirler (73). A third air swirler (83) arranged around the second air swirler (73), a fourth air swirler (93) arranged around the third air swirler (83) and a main fuel injector (86, 88) arranged radially between the third air swirler (83) and the fourth air swirler (93). A shroud (80) is arranged around the fourth air swirler (93). A downstream end (80B) of the shroud (80) is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head (48) and an upstream end (80A) of the shroud (80) is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head (48). This reduces the effects of non-uniform airflows to the fuel injectors and reduces emissions.