Abstract: Provided is a burner of double tube structure including an outer tube and an inner tube. The inner tube includes a tip-side support portion fixed on the outer tube, a base-side support portion fixed on the outer tube, a main body portion supported by the tip-side support portion, bellows interposed between the main body portion and the base-side support portion, and a bulkhead member attached at a position between the tip-side support portion and the base-side support portion. Between an outer peripheral surface of the bulkhead member and an inner peripheral surface of the outer tube, a second gap smaller than a first gap between an outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube is interposed.

Abstract: Provided is a burner of double tube structure including an outer tube and an inner tube. The inner tube includes a tip-side support portion fixed on the outer tube, a base-side support portion fixed on the outer tube, a main body portion supported by the tip-side support portion, bellows interposed between the main body portion and the base-side support portion, and a bulkhead member attached at a position between the tip-side support portion and the base-side support portion. Between an outer peripheral surface of the bulkhead member and an inner peripheral surface of the outer tube, a second gap smaller than a first gap between an outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube is interposed.

Abstract: [Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

Abstract: A gas turbine combustor includes a vane, a plurality of supports, and a pressure dynamics damping hole. The vane is disposed at the outer circumferential side of the combustion liner. The plurality of supports are disposed at an inner side of the combustion casing for fixing the vane. The pressure dynamics damping hole is formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.

Abstract: To achieve a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces. A multi-stage combustor includes a combustor liner configured to define a combustion chamber therein, a plurality of fuel nozzles configured to inject a fuel, and a manifold configured to distribute the fuel to the plurality of fuel nozzles. The manifold is disposed on a central axis of the combustor liner in a central axis extending direction. The manifold includes a casing and a plurality of partitions inserted in the casing so as to be arranged in a central axis direction of the combustor liner to define a plurality of cavities divided by the partitions. The plurality of cavities are layered in the central axis direction of the combustor liner inside of the casing, and are connected to the corresponding fuel nozzles.

Abstract: [Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

Abstract: A gas turbine combustor with a relatively simple structure is configured to attenuate pressure fluctuation owing to combustion oscillation while securing mechanical reliability. The gas turbine combustor includes a combustion liner that forms a combustion chamber for generating combustion gas, a combustion casing disposed at an outer circumferential side of the combustion liner, and a burner for supplying air flowing between the combustion liner and the combustion casing, and fuel to be supplied from a fuel supply system to the combustion chamber. The combustor further includes a vane disposed at the outer circumferential side of the combustion liner, a plurality of supports disposed at an inner side of the combustion casing for fixing the vane, and a pressure dynamics damping hole formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.

Abstract: The present invention provides a gas turbine combustor configured to form a film-like airflow around a region of a combustion liner, where pressure dynamics damping holes are formed for efficiently cooling the region where the pressure dynamics damping holes are formed without increasing concentration of discharged nitrogen oxides. The gas turbine combustor includes the combustion liner that forms a combustion chamber for receiving supply of fuel and air to generate combustion gas, a liner attached to an outer circumferential surface of the combustion liner for forming space from the outer circumferential surface, and the pressure dynamics damping hole formed in the combustion liner provided with the liner for communication between the space and the combustion chamber. The gas turbine combustor includes a cooling air guide lip disposed on an inner circumferential surface of the combustion liner for forming a film-like airflow around a region where the pressure dynamics damping hole is formed.

Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Abstract: To achieve a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces. A multi-stage combustor includes a combustor liner configured to define a combustion chamber therein, a plurality of fuel nozzles configured to inject a fuel, and a manifold configured to distribute the fuel to the plurality of fuel nozzles. The manifold is disposed on a central axis of the combustor liner in a central axis extending direction. The manifold includes a casing and a plurality of partitions inserted in the casing so as to be arranged in a central axis direction of the combustor liner to define a plurality of cavities divided by the partitions. The plurality of cavities are layered in the central axis direction of the combustor liner inside of the casing, and are connected to the corresponding fuel nozzles.

Abstract: The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.

Abstract: A combustor has at least one premixing burner for premixing fuel with air and jetting the mixed gas into a chamber for combustion. A cylinder attached to an outer circumferential portion of an end face of the burner is provided with air supply holes. An interval D1 defined between the adjacent air supply holes and an interval D2 defined between each air supply hole and the end face of the burner are each made narrower than the quenching distance in the premixed gas jetted from the premixing burner.

Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Abstract: The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.

Abstract: To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

Abstract: A gas turbine combustor comprising a burner including: a plurality of fuel nozzles to supply a fuel; a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and a swirler including a plurality of air holes to supply combustion air, characterized in that the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.

Abstract: A combustor is provided that can ensure combustion stability even when operated on low BTU gas without needing any equipment for preventing back-flow of fuel gas during operation on pilot fuel. The combustor includes a first perforated plate disposed upstream of a combustion chamber, the first plate having a plurality of nozzle holes and air holes; a second perforated plate disposed on the upstream side of the first plate; and a plurality of gas nozzles each of which is inserted into corresponding nozzle holes. The gas nozzle has a leading end located inside the corresponding one of the nozzle holes. Each of the gas nozzles includes a jet hole portion having a diameter smaller than that of a gas jet hole of the gas nozzle; and a passage portion designed to form an air passage on the outer circumference of the leading end portion of the gas nozzle.

Abstract: A gas turbine combustor stably burns low-BTU gases, such as blast furnace gases, that are heavily laden with CO2. The gas turbine combustor includes a double-swirling burner with an inner swirler and an outer swirler, the burner having a configuration with gas fuel injection holes and air injection holes arranged at alternate positions in the inner swirler and with gas injection holes arranged in the outer swirler. In addition, fuel injection holes for enhancing flame stability are provided at positions radially inward of the inner swirler. An inner flame by the inner swirler and an outer flame by the outer swirler interact with each other to stably burn the low-BTU gas. In the inner swirler, the gas injection holes and air injection holes arranged at alternate positions contributes to raising a temperature of the inner flame to a level required for flame stabilization.

Abstract: This invention is directed to supply a combustor having a structure that reduces NOx emissions while maintaining combustion stability. The combustor has a chamber into which fuel and air are supplied. An air hole plate having a plurality of air holes upstream of the chamber is also disclosed, and fuel nozzles supplying fuel to the air holes of the air hole plate are further disclosed. In the combustor, a center of a chamber-side of the air hole plate is closer to the chamber than exits of outermost peripheral air holes.

Abstract: A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. A combustor 2 according to the present invention includes a combustion chamber 5 to which fuel and air are supplied; air holes 32 adapted to supply air to the combustion chamber 5; fuel nozzles 25 adapted to supply gaseous fuel to the air holes 32; and orifices 24 adapted to allow the gaseous fuel supplied to the air holes 32 to cause a pressure drop.