Burner

摘要

The invention relates to a burner (B) of a gas turbine extending along an axis (X) and comprising in axial order
- a swirler section (SW)
- a mixing section (MX)
- an outlet section (OT)
- a main combustion zone (CZ)
- wherein said swirler section (SW) comprises swirler vanes (SWV) made to swirl a stream of fuel (F) and oxygen containing gas (OCG) entering the swirler section (SW) in a circumferential direction,
- wherein said mixing section (MX) conducts the premix (MFOCG) of fuel (F) and oxygen containing gas (OCG) to said outlet section (OT),
- wherein said outlet section (OT) discharges said premix (MFOCG) into said combustion zone (CZ) expanding the flow of premix (MFOCG) from a smaller axial cross section of said mixing section (MX) to a larger cross section of said combustion zone (CZ) which makes streamlines of said flow to diverge radially. The improve stability a surface of the outlet section (OT) facing the flow of said premix (MFOCG) is provided with first fuel nozzles (FN1) injecting fuel into said premix (MFOCG) into a radial inwardly inclined direction before the flow of said premix (MFOCG) enters said outlet section (OT) into said combustion zone (CZ).