Patent ID: 8117846

Claim:
A gas turbine burner, comprising: a radial swirler having an air inlet opening, an air outlet opening arranged downstream of the air inlet opening, and a swirler air passage extending from the air inlet opening to the air outlet opening which is delimited by swirler air passage walls formed at least partly by faces of a plurality of swirler vanes; a fuel injection system having fuel injection openings arranged in at least one face of a swirler vane so as to inject fuel into the swirler air passage; and an air injection system that comprises air injection openings arranged in at least one face of a swirler vane and arranged downstream of the fuel injection openings for injecting air downstream from the fuel injection openings into the swirler air passage, wherein the air injection openings provide additional air to the air streaming through the swirler air passage from the air inlet opening.