A burner for use in a gas turbine engine includes a burner tube having an inlet end and an outlet end; a plurality of slots formed in the burner tube and configured to introduce air flows tangentially into the burner tube and impart swirl to the air flows; a plurality of fuel passages extending axially along the burner tube; and a plurality of fuel injection holes provided to each fuel passage. At least one of the fuel injection holes of each fuel passage is configured to inject a fuel flow tangentially into the burner tube between air flows of adjacent slots to form a fuel and air co-flow. A method of mixing air and fuel in a burner of a gas turbine is provided. The burner includes a burner tube including a plurality of slots formed in the burner tube. The method includes introducing air flows tangentially into the burner tube through the slots and imparting swirl to the air flows; and injecting fuel between air flows of adjacent slots to form fuel and air co-flows. This eliminates jet cross flow, which tends to cause flame holding. The tangentially entered fuel and air co-flow layers then flow down axially with quick mixing and dump to a combustor for a stable premixed combustion.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
 This invention was made with Government support under Contract No. DE-FC26-05NT42643 awarded by the Department of Energy. The Government has certain rights in this invention.