Inclined fuel injection of fuel into a swirler slot

A combustor for a gas turbine, the combustor comprising:

• a pre-combustion chamber having a center axis,
• a swirler mounted to the pre-combustion chamber,
• wherein the swirler surrounds the pre-combustion chamber in a circumferential direction with respect to the centre axis,
• wherein the swirler comprises a bottom surface which forms a part of a slot through which an oxidant/fuel mixture is injectable into the pre-combustion chamber,
• wherein the bottom surface is located within a bottom plane,
• wherein the swirler further comprises a fuel injector which is arranged such that a fuel is injectable into the slot through the bottom surface with a fuel injection direction,
• wherein a first component of the fuel injection direction is non-parallel to a normal (n) of the bottom plane,
• wherein the fuel injector comprises an injection tube, said injection tube is aligned with respect to the bottom surface such that the fuel is injectable into the slot with the fuel injection direction, and
• wherein the fuel injector is arranged such that an injection angle (Θ) between the bottom plane and the fuel injection direction is between 20° and 70°,
• wherein the swirler comprises a vane comprising a side wall oriented transverse to the bottom surface and which forms a further part of the slot, wherein the fuel injector is arranged such that a second component of the fuel injection direction is into the slot and toward the side wall.