Gas turbine combustor
Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
1. A gas turbine combustor provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, wherein
the pilot burner includes a pilot nozzle that supplies pilot fuel, a pilot air channel that is formed around the pilot nozzle such that pilot air in the pilot air channel flows parallel to the pilot fuel flowing in the pilot nozzle to supply the pilot air thereto, and an ignition improving part that is provided in the pilot air channel and reduces the size of a low-temperature air layer of the pilot air, formed between the pilot flame and the premixed flame,
the pilot nozzle includes an injecting hole that injects the pilot fuel into the pilot burner,
the pilot air channel supplies the pilot air to the pilot burner at a location downstream of the injecting hole, and
the ignition improving part is provided in the pilot air channel at an exit of the pilot air channel, and is one or a plurality of flow-splitting members with a substantially triangular pole-shape provided on an inner peripheral surface of a cylindrical member of the pilot burner so as to project towards an inside in a radial direction with respect to the inner peripheral surface.
2. The gas turbine combustor according to claim 1 , wherein the one or the plurality of flow-splitting members is provided at an outlet of a pilot swirler.
3. The gas turbine combustor according to claim 1 , wherein the ignition improving part is provided in the pilot air channel, and the one or the plurality of flow-splitting members with the substantially triangular pole-shape is provided on the inner peripheral surface of the cylindrical member of the pilot burner at an upstream side of a downstream end of a cone part of the pilot nozzle.