Patent ID: 8033112

Claim:
A swirler for premixing a first flow of fuel and a second flow of air for use in a burner of a gas turbine engine, the swirler comprising: a plurality of fuel tubes; a first channel emerging into a combustion room of the burner that provides the combustion room with a third flow of premixed air and fuel; a plurality of swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage, wherein the plurality of swirler wings are located at an inlet of the first channel, wherein one fuel tube of the plurality of fuel tubes for gaseous fuel is positioned substantially in parallel on each side of a mixing rod in the passage so that a length of each rod lies in the same plane, wherein the plurality of fuel tubes are provided with a plurality of diffuser holes distributed along each fuel tube in a row acting as gas injectors for effectively distributing fuel in a flow of air passing through the passage and wherein each fuel tube is adjacent to one of the plurality of swirler wings.