Inclined fuel injection of fuel into a swirler slot

The present invention relates to a combustor (100) for a gas turbine. The combustor (100) comprises a pre-combustion chamber (101) having a centre axis (102) and a swirler (103) which is mounted to the pre-combustion chamber (101). The swirler (103) surrounds the pre-combustion chamber (101) in a circumferential direction with respect to the centre axis (102). The swirler (103) comprises a bottom surface (104) which forms a part of a slot (201) through which oxidant/fuel mixture is injectable into the pre-combustion chamber (101), wherein the bottom surface (104) is located in a bottom plane (106). The swirler (103) further comprises a fuel injector (107) which is arranged to the bottom surface (104) such that a fuel is injectable into the slot (201) with a fuel injection direction (108), wherein a first component of the fuel injection direction (108) is non-parallel to the normal (n) of the bottom plane (106).