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 . <EOS>