Patent ID: 7143583

Claim:
A gas turbine combustor comprising: a pilot burner; a premixed combustion burner disposed on the circumference of said pilot burner; a liner in an approximately cylindrical shape which is disposed on the downstream side of said premixed combustion burner, and which defines a combustion chamber in the liner; and a plurality of flame stabilizers radially disposed at the exit of said premixed combustion burner, said plurality of flame stabilizers being formed as a plurality of radial projections each projecting from an inner circumferential side thereof to an outer circumferential side thereof, and said plurality of flame stabilizers being arranged in a cantilever manner on said inner circumferential side such that said flame stabilizers form narrowed passages between the adjacent flame stabilizers; wherein the pilot burner is provided with a fuel injection means which ejects at least one of gas fuel and liquid fuel, and a plurality of air nozzles for injecting air into said combustion chamber are located on the outside of said pilot burner and the inside of said premixed combustion chamber.