Abstract: A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

Abstract: A premixed combustion burner including: an outer tube having an inlet opening on a first side in an axial direction and an outlet opening on a second side in the axial direction; an inner tube formed in a cylindrical shape extending in the axial direction and spaced inside the outer tube, and forming a film air flow path between the inner and outer tubes; and a strut extending inward from the inner wall surface of the outer tube and supporting the inner tube. An end of the inner tube on the first side is located further towards the second side than the outer tube inlet opening. An end of the inner tube on the second side is located further towards the first side than the outlet opening of the outer tube. The outer tube, the strut, and the inner tube are formed with a fuel injection flow path.

Abstract: A combustor includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which an air hole passing through the upstream side end face and the downstream side end face is formed in the tube plate; and a fuel injector that injects fuel into air passing through the air hole. The air hole has: a bent channel that curves toward a direction orthogonal to the combustor axis toward the downstream side; and an inclined channel that is connected to the downstream side of the bent channel so as to be continuous therewith, and that extends inclining with respect to the combustor axis and opens to the downstream side end face. A fuel injection position at which the fuel injector injects fuel is located on the downstream side of the upstream end of the bent channel.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

Abstract: A combustor of the present disclosure includes: a mixing portion which is provided with a plurality of mixing passages passing through the mixing portion so as to be extended from an upstream end surface to a downstream end surface of the mixing portion intersecting an axis of the combustor, air being introduced to the plurality of the mixing passages from the upstream end surface of the mixing portion; and a fuel supply portion which is configured to supply the air introduced to the mixing passages with fuel to generate mixed fluid, wherein flow paths of the mixing passages have different pressure loss coefficients so that the differences in the flow velocity of the mixed fluid flowing through the mixing passages at the downstream end surface of the mixing portion are greater than those of a case where the mixing passages have the same flow path shape.

Abstract: A burner assembly includes a plurality of bumers for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each fuel nozzle includes a fuel injection hole formed on a side surface of the protruding portion. At least a portion of a first air passage for flowing the air is formed inside the protruding portion. The first air passage includes: an inlet formed on a surface of the protruding portion on an upstream side of the fuel injection hole in the flow direction of the air; and an outlet formed on a side surface of the protruding portion or a passage wall of the mixing passage. At least a portion of the outlet is formed downstream of the fuel injection hole in the flow direction of the air.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each of the at least one fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each of the at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protruding portion. A top surface of the protruding portion includes a convex curved surface.

Abstract: A fuel nozzle for a gas turbine is a diffusion combustion type fuel nozzle for a gas turbine, including a nozzle body, a plurality of nozzle holes arranged along a circumferential direction of the nozzle body, each of the nozzle holes extending along an axial direction of the nozzle body and having a center axis inclined toward a center axis of the nozzle body downstream in the axial direction of the nozzle body, and a plurality of fuel supply holes extending along the axial direction of the nozzle body and connected to the plurality of nozzle holes to serve as fuel supply paths for supplying fuel, respectively. Each of the nozzle holes has an injection opening for injecting the fuel to a downstream end portion in the axial direction of the nozzle body.

Abstract: A gas turbine provided with: a first nozzle including a first-nozzle radially inner fuel injection hole from which to inject a first-nozzle fuel and a first-nozzle radially outer fuel injection hole which is formed on a radially outer side of the first nozzle relative to the first-nozzle radially inner fuel injection hole and upstream of the first-nozzle radially inner fuel injection hole with respect to the flow of air inside a combustor and from which to inject the first-nozzle fuel, and in a case where the first-nozzle fuel is made of a moderate calorie fuel, the first-nozzle fuel is constantly injected from the first-nozzle radially inner fuel injection hole while the gas turbine is driven, and the first-nozzle fuel is constantly injected from the first-nozzle radially outer fuel injection hole while the gas turbine is driven at a rated rotation speed.

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 combustion device includes: a nozzle casing defining an axial flow passage; and a nozzle disposed in the axial flow passage. The nozzle includes: a nozzle body having a tubular shape extending along the axial flow passage; a swirler vane protruding radially outward from the nozzle body in a radial direction of the nozzle body; at least one first injection hole having an opening on a surface of the nozzle body or the swirler vane; at least one second injection hole having an opening on the surface of the nozzle body or the swirler vane; a first fuel flow passage extending through the nozzle body and being in communication with the at least one first injection hole; and a second fuel flow passage extending through the nozzle body separately from the first fuel flow passage, and being in communication with the at least one second injection hole.

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 fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.

Abstract: A gas turbine controller having a first generator for setting the flow rate of fuel or air being supplied to a combustor in correspondence with a target load, a sensor for detecting intake temperature of a compressor, a second generator for setting a correction amount of a set value of fuel flow rate or air flow rate based on the value detected by the sensor, a third generator for setting a modification amount of the correction amount while taking account of the target load, a first multiplier for operating a modified correction amount from a correction amount set by the second generator and a modification amount set by the third generator, and a second multiplier for calculating the flow rate of fuel or air being supplied to a combustor by adding the modified correction amount to the set value of fuel flow rate or air flow rate.

Abstract: A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.

Abstract: Occurrence of combustion vibration is prevented in a gas turbine plant by enhancing the degree of freedom in setting an airflow rate or a fuel flow rate in correspondence with a target load thereby enhancing combustion stability.

Abstract: A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base 30. If no sufficient data is stored yet in the data base 30 for any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base 32. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.

Abstract: A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base 30. If no sufficient data is stored yet in the data base 30 for any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base 32. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.