A combustor assembly (56, 60) for a gas turbine engine comprising: a combustion chamber; a fuel injector assembly in communication with the combustion chamber, comprising: a swirler body situated about a nozzle to define an injector passage that converges to a throat, the throat defined at a distance from the combustion chamber; and wherein the nozzle includes a nozzle body, an end portion, a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector, wherein the first fuel injector axis is collinear with a nozzle longitudinal axis of the nozzle such that the primary fuel injector is situated at a terminal end of the end portion of the nozzle; wherein the injector passage includes a first passage section merging into a second passage section, the first passage section defined between the swirler body and the nozzle, and the second passage section defining the throat, wherein the at least one secondary plain-jet fuel injector defines a second fuel injector axis extending through an outlet of the secondary plain jet fuel injector, the at least one secondary plain jet fuel injector arranged such that a projection of the second fuel injector axis intersects an outer wall of the injector passage along the first passage section, wherein a radially outer wall of the first passage section slopes toward the first fuel injector axis to define a first passage angle (α), the first passage (α) angle being between about 30 degrees and about 50 degrees, wherein a radially inner wall of the first passage section slopes toward the first fuel injector axis to define a second passage angle (β), the second passage angle (β) being within about 5 degrees of the first passage angle (α), characterized in that the end portion of the nozzle has a dome shaped profile. a combustion chamber; a fuel injector assembly in communication with the combustion chamber, comprising: a swirler body situated about a nozzle to define an injector passage that converges to a throat, the throat defined at a distance from the combustion chamber; and wherein the nozzle includes a nozzle body, an end portion, a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector, wherein the first fuel injector axis is collinear with a nozzle longitudinal axis of the nozzle such that the primary fuel injector is situated at a terminal end of the end portion of the nozzle; wherein the injector passage includes a first passage section merging into a second passage section, the first passage section defined between the swirler body and the nozzle, and the second passage section defining the throat, wherein the at least one secondary plain-jet fuel injector defines a second fuel injector axis extending through an outlet of the secondary plain jet fuel injector, the at least one secondary plain jet fuel injector arranged such that a projection of the second fuel injector axis intersects an outer wall of the injector passage along the first passage section, wherein a radially outer wall of the first passage section slopes toward the first fuel injector axis to define a first passage angle (α), the first passage (α) angle being between about 30 degrees and about 50 degrees, wherein a radially inner wall of the first passage section slopes toward the first fuel injector axis to define a second passage angle (β), the second passage angle (β) being within about 5 degrees of the first passage angle (α), characterized in that the end portion of the nozzle has a dome shaped profile. a swirler body situated about a nozzle to define an injector passage that converges to a throat, the throat defined at a distance from the combustion chamber; and wherein the nozzle includes a nozzle body, an end portion, a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector, wherein the first fuel injector axis is collinear with a nozzle longitudinal axis of the nozzle such that the primary fuel injector is situated at a terminal end of the end portion of the nozzle; wherein the injector passage includes a first passage section merging into a second passage section, the first passage section defined between the swirler body and the nozzle, and the second passage section defining the throat, wherein the at least one secondary plain-jet fuel injector defines a second fuel injector axis extending through an outlet of the secondary plain jet fuel injector, the at least one secondary plain jet fuel injector arranged such that a projection of the second fuel injector axis intersects an outer wall of the injector passage along the first passage section, wherein a radially outer wall of the first passage section slopes toward the first fuel injector axis to define a first passage angle (α), the first passage (α) angle being between about 30 degrees and about 50 degrees, wherein a radially inner wall of the first passage section slopes toward the first fuel injector axis to define a second passage angle (β), the second passage angle (β) being within about 5 degrees of the first passage angle (α), characterized in that the end portion of the nozzle has a dome shaped profile.