Abstract: A combustor includes: a combustor basket configured to surround a fuel nozzle from an outer circumferential side, and a plurality of connecting members formed in a circumferential direction at intervals to connect a rear end of the combustor basket and a casing and configured to define a flow path through which compressed air introduced into the combustor basket flows. A circulation direction of the compressed air flowing through the flow path is configured to be reversed at a rear end of the combustor basket and the compressed air is introduced into the fuel nozzle. The flow path is partially or entirely inclined in the circumferential direction to blow the compressed air.

Abstract: A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.

Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).

Abstract: A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).

Abstract: Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79?Dout/Din?0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.

Abstract: Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NOx emissions of gas turbine combustors. The gas turbine combustion burner includes a plurality of swirling vanes (20) for ejecting fuel from fuel ejection holes (23, 24) into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle (21) having the swirling vanes (20) arranged radially on an outer circumferential surface thereof and having a first fuel passage (26), through which the fuel is guided to the fuel ejection holes (23, 24), provided therein, a cavity (25) communicating with the fuel ejection holes (23, 24) is provided in each swirling vane (20), and at least two second fuel passages (27) are provided between the cavity (25) and the first fuel passage (26) along an axial direction.

Abstract: Provided is a combustor that is made compact and achieves NOx reduction.

Abstract: A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has a fuel nozzle, a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle, and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle. The swirler vanes gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vanes.

Abstract: Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet (222) is set within a range of 0.79?Dout/Din?0.9, relative to a cross-sectional area (Din) of a transition piece inlet (221) of a combustor (2), and in a first stage turbine nozzle (321) of a turbine (3) connected to the transition piece outlet (222), a size (Hin) in a radial direction of an upstream opening is matched with a size (a) in a radial direction of the transition piece outlet (222). In a combustor transition piece (22) that is included in the combustor (2) having a center line (S) arranged with an angle to an axial center (R) of a rotor (4) of a gas turbine and that guides combustion gas to the turbine (3), a cross-sectional area is monotonously reduced from the transition piece inlet (221) in which the combustion gas flows to the transition piece outlet (222) from which the combustion gas flows out.

Abstract: A premixed combustion burner for a gas turbine is provided that can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has: a fuel nozzle; a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle; and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle and that gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vane.

Abstract: A surface processing method of processing a surface of a substrate includes disposing the substrate in a vacuum chamber, processing by applying a high-frequency voltage to the substrate and by sputtering the surface of the substrate, measuring a cathode drop potential generated at the substrate in the processing and obtaining a time integration value of the cathode drop potential, and determining whether or not a processed state of the surface of the substrate is good based on the time integration value obtained in the measuring.