A gas turbine combustor comprising: a primary fuel injector and a secondary fuel injector (100, 200) downstream thereof, an axial fuel staging system comprising: a system (160, 260) for dissipating fuel egress, the system comprising: a fuel supply assembly having a fuel supply line providing fuel and a purge air conduit arranged co-axially around the fuel supply line, thereby defining an annular channel around the fuel supply line; the secondary fuel injector (100, 200) for the combustor, said fuel injector (100, 200) including a perimeter body (110, 210) defining a portion of the fuel injector (100, 200), a fuel injection port 116, 226) associated with the perimeter body (110, 210), and an internal mixing chamber (176, 282) downstream of the fuel injection port (116, 226) in a direction of fuel flow; wherein the fuel supply line provides fuel to the fuel injection port (116, 226); and wherein the perimeter body (110, 210) of the fuel injector (100, 200) defines a fuel egress passage (162, 262) therethrough, the fuel egress passage (162, 262) having an inlet (161, 261) in fluid communication with the annular channel and an outlet (168, 268) in fluid communication with the mixing chamber (176, 282) and downstream of the fuel injection port; the perimeter body (110, 210) further defining a fuel purge cavity (164, 264) therein, the fuel purge cavity (164, 264) being located between the inlet (161, 261) and the outlet (168, 268) of the fuel egress passage (162, 262); and the fuel egress passage (162, 262) including a first portion (163, 263) upstream of the fuel purge cavity (164, 264) and a second portion (166, 266) downstream of the fuel purge cavity (164, 264), the first portion (163, 263) including the inlet (161, 261) and the second portion (166, 266) including the outlet (168, 268). an axial fuel staging system comprising: a system (160, 260) for dissipating fuel egress, the system comprising: a fuel supply assembly having a fuel supply line providing fuel and a purge air conduit arranged co-axially around the fuel supply line, thereby defining an annular channel around the fuel supply line; the secondary fuel injector (100, 200) for the combustor, said fuel injector (100, 200) including a perimeter body (110, 210) defining a portion of the fuel injector (100, 200), a fuel injection port 116, 226) associated with the perimeter body (110, 210), and an internal mixing chamber (176, 282) downstream of the fuel injection port (116, 226) in a direction of fuel flow; a fuel supply assembly having a fuel supply line providing fuel and a purge air conduit arranged co-axially around the fuel supply line, thereby defining an annular channel around the fuel supply line; the secondary fuel injector (100, 200) for the combustor, said fuel injector (100, 200) including a perimeter body (110, 210) defining a portion of the fuel injector (100, 200), a fuel injection port 116, 226) associated with the perimeter body (110, 210), and an internal mixing chamber (176, 282) downstream of the fuel injection port (116, 226) in a direction of fuel flow; wherein the fuel supply line provides fuel to the fuel injection port (116, 226); and wherein the perimeter body (110, 210) of the fuel injector (100, 200) defines a fuel egress passage (162, 262) therethrough, the fuel egress passage (162, 262) having an inlet (161, 261) in fluid communication with the annular channel and an outlet (168, 268) in fluid communication with the mixing chamber (176, 282) and downstream of the fuel injection port; the perimeter body (110, 210) further defining a fuel purge cavity (164, 264) therein, the fuel purge cavity (164, 264) being located between the inlet (161, 261) and the outlet (168, 268) of the fuel egress passage (162, 262); and