A combustor for a gas turbine engine, the combustor comprising: a combustion chamber defined between an inner shell and an outer shell; a hood chamber separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell, the bulkhead comprising at least one opening extending between the hood chamber and the combustion chamber; a fuel injector extending through the at least one opening, the fuel injector comprising a primary fuel passage comprising a primary fuel outlet located within the combustion chamber, the fuel injector further comprising a secondary fuel passage comprising a plurality of secondary fuel outlets located upstream of the primary fuel outlet along a fuel injector plane upstream of the bulkhead; and a swirler extending through the at least one opening and located radially outside of the fuel injector with respect to a fuel injector center axis, the swirler comprising a swirler exit plane defined by a downstream end of the swirler, wherein a downstream end of the fuel injector comprises a tip surface, wherein the tip surface is disposed downstream of the bulkhead, wherein: the swirler exit plane is disposed within the combustion chamber downstream of the bulkhead; and the primary fuel outlet is located at or downstream of the swirler exit plane and in a center of the tip surface, characterised in that the tip surface is located at the swirler exit plane and the tip surface is disposed along and parallel to the swirler exit plane. a combustion chamber defined between an inner shell and an outer shell; a hood chamber separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell, the bulkhead comprising at least one opening extending between the hood chamber and the combustion chamber; a fuel injector extending through the at least one opening, the fuel injector comprising a primary fuel passage comprising a primary fuel outlet located within the combustion chamber, the fuel injector further comprising a secondary fuel passage comprising a plurality of secondary fuel outlets located upstream of the primary fuel outlet along a fuel injector plane upstream of the bulkhead; and a swirler extending through the at least one opening and located radially outside of the fuel injector with respect to a fuel injector center axis, the swirler comprising a swirler exit plane defined by a downstream end of the swirler, wherein a downstream end of the fuel injector comprises a tip surface, wherein the tip surface is disposed downstream of the bulkhead, wherein: the swirler exit plane is disposed within the combustion chamber downstream of the bulkhead; and the primary fuel outlet is located at or downstream of the swirler exit plane and in a center of the tip surface, characterised in that the tip surface is located at the swirler exit plane and the tip surface is disposed along and parallel to the swirler exit plane. the swirler exit plane is disposed within the combustion chamber downstream of the bulkhead; and the primary fuel outlet is located at or downstream of the swirler exit plane and in a center of the tip surface, characterised in that the tip surface is located at the swirler exit plane and the tip surface is disposed along and parallel to the swirler exit plane.