Abstract: A gas turbine combustor includes a pilot burner, a plurality of main burners disposed around the main burners on the radially outer side. Each of the main burners (2) includes an extension tube disposed at the downstream end. The outlet of the extension tube is shaped to have a radial edge which is parallel to the radial direction. In this manner, occurrence of flashback is effectively prevented.

Abstract: A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.

Abstract: A gas turbine combustor includes a pilot burner, a plurality of main burners disposed around the main burners on the radially outer side. Each of the main burners (2) includes an extension tube disposed at the downstream end. The outlet of the extension tube is shaped to have a radial edge which is parallel to the radial direction. In this manner, occurrence of flashback is effectively prevented.

Abstract: A combustor of a gas turbine, which is composed of an inner tube and a transition pipe connected together, comprising: an internal swirler composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring; and an external swirler composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring, the internal swirler and the external swirler being disposed within the inner tube.

Abstract: The present invention relates to a gas turbine combustor comprising an air passage to supply air to the inside; and a fuel nozzle which is provided with an injection port to inject fuel and disposed in the air passage, wherein a turbulence producing means adjacent to the injection port of the fuel nozzle is provided in the air passage. Further, the present invention relates to a gas turbine combustor comprising an air passage to supply air to the inside; and a fuel nozzle which is provided with an injection port to inject fuel and disposed in the air passage, wherein a diffuser portion is provided in the air passage, and the diffuser portion causes the cross-sectional area of a part of the air passage positioned in the vicinity of the injection port to be smaller than that of a downstream portion of the air passage positioned downstream from the injection port in the direction of the airflow. Thus, the mixing action of fuel and air can be enhanced, and combustion vibration can be prevented.

Abstract: The present invention relates to a gas turbine combustor comprising an air passage to supply air to the inside; and a fuel nozzle which is provided with an injection port to inject fuel and disposed in the air passage, wherein a turbulence producing means adjacent to the injection port of the fuel nozzle is provided in the air passage. Further, the present invention relates to a gas turbine combustor comprising an air passage to supply air to the inside; and a fuel nozzle which is provided with an injection port to inject fuel and disposed in the air passage, wherein a diffuser portion is provided in the air passage, and the diffuser portion causes the cross-sectional area of a part of the air passage positioned in the vicinity of the injection port to be smaller than that, of a downstream portion of the air passage positioned downstream from the injection port in the direction of the airflow. Thus, the mixing action of fuel and air can be enhanced, and combustion vibration can be prevented.

Abstract: This invention relates to a fuel discharge member which can reduce the amount of NOx exhaust. The fuel discharge member is fixed on a fuel supply conduit, and comprises: a main body having an internal space which communicates with a fuel passage in the fuel supply conduit, fuel discharge outlets which communicate with the internal space, and a trailing edge. The thickness of the trailing edge is no more than 5 mm, or a flow passage block ratio of the fuel discharge member is no more than 10% with respect to the cross-sectional area of the air flow passage in which the fuel discharge member is to be placed. Alternatively, the main body is a flat tube.