Patent ID: 11885498
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine, comprising:
a compressor section;
a turbine section;
a combustion section located downstream from the compressor section and upstream from the turbine section and having a combustion chamber extending between a dome inlet and a combustor outlet;
a primary fuel injector fluidly coupled to the dome inlet;
a second fuel injector fluidly coupled to the combustion chamber at a location downstream of the dome inlet and upstream of the combustor outlet;
a structural element defining the second fuel injector and extending radially at least partially into the combustion chamber and axially between a structural element leading edge and a structural element trailing edge, the structural element separating the combustion chamber into a primary zone downstream from the primary fuel injector and a secondary zone downstream of the structural element trailing edge, wherein the structural element includes a set of openings arranged along the structural element leading edge; and
a fuel system fluidly coupled to the combustion section, the fuel system comprising:
a fuel supply;
a primary fuel line fluidly coupling the fuel supply to the primary fuel injector;
a catalytic endothermic reformer fluidly coupled to the fuel supply; and
a secondary fuel line fluidly coupling the catalytic endothermic reformer to the second fuel injector.