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A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is ch

A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.

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What is claimed is: 1. 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

What is claimed is: 1. 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. 2. The gas turbine combustor according to claim 1, further comprising a cross-fire tube provided with an opening which is disposed at the side wall of said liner and which is circumferentially aligned with one of said flame stabilizers. 3. The gas turbine combustor according to claim 1, wherein said flame stabilizers are each inclined so that the outer circumferential side thereof is positioned on the downstream side relative to the inner circumferential side thereof at the edge thereof on the downstream side, and the inclination angle of the flame stabilizer is 30째 or more and 60째 or less relative to the center axis of the combustor. 4. The gas turbine combustor according to claim 1, wherein the inner circumferential sides of said flame stabilizers are fixed to said premixed combustion burner, and edges, on the outer periphery side, of said flame stabilizers are separated from the outer circumferential wall of said premixed combustion burner. 5. The gas turbine combustor according to claim 1, wherein said air nozzle is configured in such a manner as to spout out air swirlingly. 6. A gas turbine combustor comprising: a pilot burner; a premixed combustion burner disposed on the circumferential 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 flame stabilizers being formed as a plurality of radial projections each projecting from an inner circumferential side thereof to an outer circumferential side thereof; 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 the combustion chamber are located on the outside of said pilot burner and the inside of said premixed combustion chamber; wherein a slit is provided outside said air nozzle and inside said premixed combustion burner, and a means of allowing air to flow toward the flame stabilizer is provided in said slit. 7. The gas turbine combustor according to claim 1, wherein an air inlet portion or an air outlet portion of said pilot burner is provided with a nozzle capable of ejecting water or steam. 8. The gas turbine combustor according to claim 1, further comprising a partition which divides a passage of said premixed combustion burner in the circumferential direction. 9. A gas turbine combustor comprising: a pilot burner which is provided with a fuel injection means capable of injecting gas fuel and liquid fuel; a premixed combustion burner disposed in the outer 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 inner wall; 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 said flame stabilizers are slantly disposed so that the outer circumferential side thereof is positioned on the downstream side thereof relative to the inner circumferential side at the edge, on the downstream side, of the flame stabilizer, said flame stabilizers are fixed to said premixed combustion burner on the inner circumferential side, and edges, on the outer circumferential side, of said flame stabilizers are separated from the outer circumferential wall of said premixed combustion burner. 10. A combustion method of a gas turbine combustor including a pilot burner, a premixed combustion burner disposed on the outer circumference of said pilot burner, and 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 inner wall, comprising the steps of: disposing a plurality of flame stabilizers radially 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; injecting at least one of gas fuel and liquid fuel from said pilot burner; and spouting out air into said combustion chamber from a plurality of air nozzles disposed outside said pilot burner and inside said premixed combustion burner. 11. A method of remodeling a gas turbine combustor comprising: a pilot burner which is provided with a fuel injection means capable of injecting gas fuel and liquid fuel; a premixed combustion burner disposed within a premixed fuel passage on the outer circumference of said pilot burner; and a combustor liner in an approximately cylindrical shape which is disposed on the downstream side of said premixed combustion burner, and which defines a combustion chamber therein; said method characterized in that a plurality of flame stabilizers are 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, said flame stabilizers are slantly disposed so that the outer circumferential side thereof is positioned on the downstream side thereof relative to the inner circumferential side, and edges on the outer circumferential side of said flame stabilizers and outer circumferential wall of said premixed combustion burner are disposed so as to define a space between said edges and said outer circumferential wall. 12. A premixed type gas turbine combustor comprising: a pilot burner; an annular premixed fuel passage disposed on the outer circumference of said pilot burner; and a combustor liner in an approximately cylindrical shape which is disposed on the downstream side of said annular premixed fuel passage, and which defines a combustion chamber therein; wherein said premixed type gas turbine combustor comprises a plurality of means for making said annular premixed fuel passage facing said combustion chamber narrow in the circumferential direction to form a plurality of narrowed passages in said annular premixed fuel passage facing said combustion chamber, and said annular premixed fuel passage facing said combustion chamber is configured such that fluids in said plurality of narrowed passages formed in said annular premixed fuel passage by said means are directed toward the center side of the combustor, and intersect fuel spouted out from said pilot burner.