Abstract: A gas turbine combustor includes multiple aft frames each having a floating seal that seals a gap between an aft frame and a gas turbine in inner and outer peripheries of the aft frame, and a side seal that seals a gap between the aft frames adjacent to each other in a circumferential direction, and a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, seals air leaking from at least the gap portion into the gas turbine side, and is independent of the floating seal and the side seal.

Abstract: A combustor includes a plurality of fuel nozzles installed so as to be extended in a direction of a nozzle axis and configured to inject fuel toward one side in the direction of the nozzle axis, a pipe plate having a plurality of air holes formed therein so as to be extended in the direction of the nozzle axis, in which the air hole has an inner diameter larger than a tip end portion of the fuel nozzle and the tip end portions are respectively inserted into the air holes, and a step surface formed at a position of the tip end portion closer to the other side in the direction of the nozzle axis than a tip end surface of the tip end portion so as to be expanded in a radial direction with respect to the nozzle axis from a tip end outer peripheral surface.

Abstract: There are provided transition piece cooling holes which make NOx reduction and combustion performance improvement possible while effectively cooling the transition piece end frame and the first-stage stator vane end wall. The transition piece cooling holes include a transition piece which guides combustion gas from a combustor to a turbine, a transition piece end frame which is installed on a turbine-side outlet of the transition piece and is disposed so as to face a first-stage stator vane end wall of the turbine with a predetermined gap being interposed, and a seal member which is fitted on the transition piece end frame and is fitted into the first-stage stator vane end wall so as to seal cooling air which is supplied into the gap. The cooling holes are made in the transition piece end frame so as to directly supply the cooling air to the first-stage stator vane end wall.

Abstract: In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.

Abstract: A deviation of fuel injection amounts among a plurality of fuel nozzles connected to one fuel header is suppressed while suppressing increases in a manufacturing man-hour count and a pressure loss of a fuel. A gas turbine combustor includes: a liner forming a combustion chamber; a plurality of fuel nozzles; a fuel header to which the plurality of fuel nozzles are connected; and a fuel supply flow passage connected to the fuel header, the fuel header including a first chamber to which the fuel supply flow passage is connected and a second chamber to which the plurality of fuel nozzles are connected. An outlet of the fuel supply flow passage is opened in the first chamber, and at least one communication opening communicating with the first chamber is opened in the second chamber. The outlet of the fuel supply flow passage faces an inner wall surface of the first chamber.

Abstract: A gas turbine combustor includes multiple aft frames each having a floating seal that seals a gap between an aft frame and a gas turbine in inner and outer peripheries of the aft frame, and a side seal that seals a gap between the aft frames adjacent to each other in a circumferential direction, and a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, seals air leaking from at least the gap portion into the gas turbine side, and is independent of the floating seal and the side seal.

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: In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.

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: 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: 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: 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 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: A gas turbine combustor 2 according to the present invention comprises: a combustion chamber 50 in which fuel is burned with air to generate combustion gas; a plurality of fuel nozzles 30 arranged in multiple concentric annular rows; a first plate 32 arranged downstream of the fuel nozzles 30 and having multiple concentric circular air hole rows made up of a plurality of air holes corresponding to the fuel nozzles 30; a second plate 33 arranged downstream of the first plate 32 and having multiple air hole rows corresponding to the air hole rows of the first plate 32; and a partition wall part 37 which partitions a space part 46 between the first plate 32 and the second plate 33 into rooms corresponding to the air hole rows.

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 can suppress an increase in NOx emission from a combustor even when degradation of compressor efficiency occurs due to a decrease in performance with long-term use. The 2-shaft gas turbine has a gas generator and a power turbine, and includes a controller configured to set, in accordance with a degree of degradation of compressor efficiency computed from 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. The controller is configured 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 gas turbine combustor includes: an inner casing; an outer casing; an annular flow path disposed between the inner casing and the outer casing; a fuel header; a plurality of fuel nozzles supported concentrically on the fuel header; an air hole plate having a plurality of air holes associated with the respective fuel nozzles; a guide having a wall portion and a bent portion; and an outer peripheral flow path defined between the outer peripheral surface of the air hole plate and the inner casing.

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: A gas turbine combustor 2 according to the present invention comprises: a combustion chamber 50 in which fuel is burned with air to generate combustion gas; a plurality of fuel nozzles 30 arranged in multiple concentric annular rows; a first plate 32 arranged downstream of the fuel nozzles 30 and having multiple concentric circular air hole rows made up of a plurality of air holes corresponding to the fuel nozzles 30; a second plate 33 arranged downstream of the first plate 32 and having multiple air hole rows corresponding to the air hole rows of the first plate 32; and a partition wall part 37 which partitions a space part 46 between the first plate 32 and the second plate 33 into rooms corresponding to the air hole rows.

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, with each pair of devices generating vortices having rotational directions opposed to each other.