A combustor (36) for a gas turbine, the combustor (36) comprising a combustor axis (44) about which is arranged in flow sequence a radial swirler (40), a pre-chamber (42) and a combustion chamber (38). The radial swirler (40) comprises a base plate (45), an annular array of swirler vanes (46), defining swirler slots (47), arranged around the base plate (45), a main fuel injector (48A, 48B) for injecting a main fuel and a pilot fuel injector (50) for injecting a pilot fuel. The combustor comprises a premixer nozzle (70) located on the combustion chamber (38). The premixer nozzle (70) comprising a housing (78), an array of tubes (80) within the housing (78) and a first fuel gallery (72) for supplying a first fuel (83). Each tube (80) of the array of tubes (80) comprising an inlet (86), an outlet (88), a first aperture (90) and a second aperture (92). The first fuel gallery (72) is arranged to supply the first fuel (83) to the first aperture (90) and / or the second aperture (92). In use, air (34) is supplied to the combustor and a first portion of the air (34A) passes through the radial swirler (40) and a second portion of the air (34B) passes through the tubes (80) of the array of tubes (80) from inlet (86) to outlet (88) and mixes with the first fuel (83) that passes through the first aperture (90) and / or the second aperture (92).