Patent ID: 8065880

Claim:
A premixed combustion burner for a gas turbine comprising: a fuel nozzle; a burner cylinder arranged so as to surround said fuel nozzle and form an air passageway between itself and said fuel nozzle; and a plurality of swirler vanes arranged along an axial direction of said fuel nozzle in a plurality of positions around a circumferential direction of an outer circumference surface of said fuel nozzle and that gradually curve from an upstream side to a downstream side to spin air traveling within the air passageway from the upstream side to the downstream side, wherein each of said swirler vanes has a forward section located at the upstream side that is connected to said fuel nozzle and a rear section located at the downstream side that has a cutaway section provided at a rear edge section on an inner circumference side, wherein said cutaway section provides a gap between the rear edge section of each of said swirler vanes and the outer circumference surface of said fuel nozzle.