Abstract: A fuel injector includes: a flat tube disposed over an aperture of a wall of a combustor that extends toward a turbine in a gas turbine system. The flat tube is configured such that air compressed by a compressor of the gas turbine system flows perpendicular to a thickness direction of the flat tube before flowing through the aperture. The flat tube has a fuel hole through which gaseous fuel that flows inside the flat tube exits to a passage of the air. An entire length of a downstream edge of the flat tube with respect to a flow of the air is disposed within the aperture when viewed perpendicular to the wall.

Abstract: A wire harness includes a first harness and a second harness having a plurality of branch lines. The first harness and the second harness are combined and bound, and each of terminals of the first harness and the second harness is extended radially. Exteriors of the first harness and the second harness are removed within a combination range of the first harness and the second harness. The first harness extends across near a base end of one branch line of the second harness, and is bound with a tape near a branch portion together with a vicinity of a base end of another branch line in a juxtaposed state.

Abstract: A wire harness includes a first harness and a second harness having a plurality of branch lines. The first harness and the second harness are combined and bound, and each of terminals of the first harness and the second harness is extended radially. Exteriors of the first harness and the second harness are removed within a combination range of the first harness and the second harness. The first harness extends across near a base end of one branch line of the second harness, and is bound with a tape near a branch portion together with a vicinity of a base end of another branch line in a juxtaposed state.

Abstract: A combustor includes: a fuel nozzle extending along an axis; a tubular combustor basket configured to cover the fuel nozzle; and a tubular transition piece configured to define a cooling air passage through which air from outside is introduced between the tubular transition piece and an outer circumferential surface of a leading end portion of the tubular combustor basket. The tubular transition piece extends toward a leading end side of the tubular combustor basket.

Abstract: A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction.

Abstract: A combustor includes: a fuel nozzle extending along an axis; a tubular combustor basket configured to cover the fuel nozzle; and a tubular transition piece configured to form a cooling air passage through which air from the outside is introduced between the transition piece and an outer circumferential surface of a leading end portion in the combustor basket and extending toward the leading end side of the combustor basket, wherein a position in a radial direction of the leading end of the combustor basket partially varies in a circumferential direction. Thus, vortices are formed on the downstream side of the leading end of the combustor basket. This vortex expedites mixing of air supplied through the cooling air passage with a combustion gas.

Abstract: A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction.

Abstract: The liquid fuel-using gas turbine combustor prevents the generation of combustion oscillation. The gas turbine combustor is provided with a pilot burner disposed on the central position of the combustion casing, main burners disposed so as to surround the pilot burner. The main burners are configured such that a main nozzle is installed in the central portion of a cylindrical premixing nozzle, with a liquid fuel being injected from fuel injection holes (provided at the periphery of the main nozzle) toward the inner surface of an elongated nozzle connected to the downstream side of the premixing nozzle, and with the injection pattern of the fuel being set so as to differ among the multiple main burners. For example, different injection patterns can be provided by setting different liquid fuel injection angles (?1, ?2) for the fuel injection holes on the multiple main burners.