Abstract: A gas turbine combustor includes a tubular combustion liner that has a plurality of dilution holes disposed circumferentially at a section downstream in a direction of flow of combustion gas, a combustor casing that encloses the combustion liner, a liner flow sleeve disposed between the combustion liner and the combustor casing, to define with the combustion liner an air flow path through which compressed air flows, the liner flow sleeve having a plurality of steam injection holes, and a steam distribution mechanism disposed on an outer peripheral side of the liner flow sleeve. The steam distribution mechanism distributes received injection steam to the steam injection holes. At least some of the steam injection holes are disposed so to face at least some of the dilution holes. The steam injection holes facing the respective dilution holes are each formed so as to spurt the injection steam toward the corresponding dilution hole.

Abstract: A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units. A fuel ratio, at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.

Abstract: In a perforated coaxial jet burner implemented by a lot of air-fuel coaxial jets, a swirl plate (33) as an end face of the burner on the combustion chamber's side has a lot of air holes for supplying unburned premixed gas of fuel and air to the combustion chamber. Grooves (36) are formed downstream of the air holes of the swirl plate. Adhesion of flame to the swirl plate is inhibited by feeding part of the unburned premixed gas to the grooves. Further, the width of each remaining part (37) between adjacent grooves is set at several millimeters that is approximately equal to the flame quenching distance, by which adhesion of flame to the remaining parts is also prevented. With this configuration, both stable combustion and low NOx combustion can be achieved irrespective of the load condition.

Abstract: A two-shaft gas turbine is provided which includes: a compressor; a combustor having multiple fuel systems and generating combustion gas by combusting fuels from the fuel systems and air compressed by the compressor; a high-pressure turbine coupled coaxially with the compressor and rotated by the combustion gas; a low-pressure turbine having a shaft structure independent of the high-pressure turbine and rotated by exhaust gas from the high-pressure turbine; an air extraction channel for extracting the air compressed by the compressor; an injection flow channel for feeding the air extracted through the air extraction channel back to the combustor; and a controller for controlling the flow rate of the fuel supplied to each of the fuel systems based on the air flow rate of the compressor, on the flow rate of the fuel supplied to the combustor, and on the temperature of the air in the injection flow channel.

Abstract: Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object.

Abstract: This invention provides a gas turbine power generation equipment adapted to prevent step out of an electric power generator due to a system trouble such as a momentary power failure in a local grid including intermittent renewable energy generation equipment and the gas turbine power generation equipment. The gas turbine power generation equipment that supplies electric power in cooperation with the intermittent renewable energy generation equipment in the local grid interconnected to a power grid includes: a fuel flow control valve that controls a flow rate of fuel supplied to a combustor; a bleed valve or inlet air flow control valve that controls a flow rate of air compressed by a compressor and supplied to the combustor; and a control unit configured so that if voltage on the power grid decreases below a threshold V(t), the control unit outputs a control signal to at least one of the fuel flow control valve, the bleed valve, and the inlet air flow control valve.

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.

Abstract: A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units. A fuel ratio, at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.

Abstract: A 2-shaft gas turbine is provided that can suppress an increase in NOx emission from a combustor even when degradation of a compressor efficiency occurs due to decrease in performance with long-term use. The 2-shaft gas turbine having a gas generator and a power turbine includes: means for measuring control parameters of the compressor; and a controller configured to set, in accordance with the degree of the degradation of the compressor efficiency computed from the measured control parameters, a target speed of the gas generator at a level lower than a target speed in a state where degradation of the compressor efficiency has not occurred, and to control the rotating speed of the gas generator on the basis of a difference between the target speed thus set and an actual rotating speed.

Abstract: A variable heat/power ratio cogeneration system is provided that is capable of suppressing NOx emissions to a minimum while ensuring stability of combustion of a gas turbine combustor even when the ratio of gasification gas to normal fuel (e.g., natural gas or light fuel oil) to be used is changed or the composition of the gasification gas fuel is changed. The system includes a first steam system injecting extra steam upstream of the flame zone; a second steam system branched from the first system and injecting extra steam downstream of the flame zone; first and second steam flow rate control valves controlling steam injected by first and steam systems, respectively; and a controller that controls first and second control valves based on (1) flow rates of the gasification gas and normal fuel and (2) demanded steam.

Abstract: An object of the present invention is to provide a gas turbine combustor that can suppress an increase in pressure loss while improving product reliability. The gas turbine combustor includes a combustor liner, an air transfer casing installed on the outer circumference of the combustor liner, the combustor liner and the air transfer casing defining an annular passage therebetween adapted to allow a heat-transfer medium to flow therethrough, and a plurality of vortex generating devices disposed on an inside surface of the air transfer casing, the vortex generating devices generating longitudinal vortices each having a rotational axis extending in a flow direction of a heat-transfer medium. The plurality of vortex generating devices are arranged in paired manner, each pair of devices generating vortices having rotational directions opposed to each other.

Abstract: Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent.

Abstract: An object of the present invention is to provide a combustor having a premixing burner, wherein a conical flame can be formed and the metal temperature at a liner and a burner end face can be reduced. The combustor has at least one premixing burners for premixing fuel with air and jetting the mixed gas into a chamber for combustion. A cylindrical guide 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 outlet end face of the burner are each made narrower than the quenching distance in the premixed gas jetted from the premixing burner.

Abstract: Disclosed is a gas turbine combustor equipped with a burner constructed to fire a plurality of combustors at the same time at a fuel/air ratio suitable for gas turbine ignition. A plurality of supports mounted for fixing an air injection hole plate to the combustor are provided at substantially the same phase position as that of cross fire tubes, and combustion air allocations are adjusted. Thus, flame propagation during gas turbine ignition is accelerated and all combustor cans are fired. In addition, porous plates are disposed downstream of the supports and the combustion air allocations are readjusted. Furthermore, air injection holes proximate to the cross fire tubes are particularly reduced in diameter to further adjust the combustion air allocations.

Abstract: Provided in one embodiment is a two-shaft gas turbine that exhibits improved reliability, output power, and efficiency. The turbine operates stably by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system, in which the flow rate of a fluid flowing into a combustor is higher than a simple cycle gas turbine. A portion of the fluid driving the high-pressure turbine is allowed to flow not into the high-pressure turbine but into a low-pressure turbine.

Abstract: An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen.

Abstract: Motive power supply equipment for a natural gas liquefaction plant includes gas turbine equipment having a compressor for compressing air, a combustor for generating combustion gases by burning a fuel and the compressed air from the compressor, and a turbine rotated by the combustion gases from the combustor. A low-temperature heat source supply system is provided which, during rated load operation of the gas turbine equipment, supplies carbon dioxide as a cooling medium to the gas turbine equipment in order to cool the gas turbine equipment. The carbon dioxide supplied is generated by separation from the natural gas in the natural gas purification equipment.

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.

Abstract: A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units. A fuel ratio, at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.