FUEL DELIVERY SYSTEM FOR A COMBUSTOR

A fuel delivery system (700b; 700c; 800b; 800c) for a combustor (300) of a gas turbine engine (20) including a primary fuel tank (518) configured to store a primary fuel (510), a secondary fuel tank (558) configured to store a secondary fuel (550), a swirler (326) configured to produce a main flame within a combustion chamber (302) of the combustor, and a fuel nozzle (322) configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet (323) that is located proximate to an end (328) of the swirler or at the end of the swirler, the end of the swirler being located at an inlet (306) of the combustor. The fuel delivery system also includes a primary fuel line (512) fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line (552) fluidly connecting the secondary fuel tank to the swirler.