Patent ID: 9664393
Date: 2017-05-30
CPC Classifications: F23D,F23R

Claim:
1. 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), and 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) is configured to conduct a premix (MFOCG) of the fuel (F) and oxygen containing gas (OCG) to said outlet section (OT), wherein said outlet section (OT) is configured to discharge said premix (MFOCG) into said main combustion zone (CZ) expanding a flow of premix (MFOCG) from a smaller axial cross section of said mixing section (MX) to a larger cross section of said main combustion zone (CZ) which makes streamlines of said flow to diverge radially, wherein a surface of the outlet section (OT) facing the flow of said premix (MFOCG) is provided with first fuel nozzles (FN wherein said outlet section (OT) comprises an annular rim (R) protruding into said main combustion zone (CZ) comprising second fuel nozzles (FN wherein the outlet section (OT) further comprises one mutual channel for the first fuel nozzles (FN