Abstract: Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler including a combustion chamber and configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange with the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the combustion chamber passes, and a first air preheater configured to pass second combustion gas discharged from the first water heat exchanger and to pass air supplied to the boiler.

Abstract: A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.

Abstract: A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.

Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

Abstract: A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages.

Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.

Abstract: A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NH2 radicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or N2O in the emissions to non-polluting products, mainly water and nitrogen.

Abstract: A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). The compressor-combustor (20) comprises an array of rotor blades (26). The walls of the blades (26) define a plurality of chambers (28, 30). Each chamber (28, 30) has a flow inlet (32) to receive fluid from the radial compressor (16), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (20). The plurality of chambers (28, 30) comprises a first pilot combustion chamber (28a) and a second pilot combustion chamber (28b). The first pilot combustion chamber (28a) is provided with a first fuel injector (40a), and the second pilot combustion chamber (28b) is provided with a second fuel injector (40a).

Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

Abstract: A combined cycle power plant that includes a first gas turbine engine including a first turbine section, a second gas turbine engine including a second turbine section having an aft outlet configured to discharge an exhaust gas stream, an emissions reduction system configured to receive the exhaust gas stream discharged from the second gas turbine engine, and configured to remove oxides of nitrogen from the exhaust gas stream, and an interstage extraction system communicatively coupled with the first turbine section. The interstage extraction system is configured to selectively extract turbine extraction air from the first turbine section for providing heat to the emissions reduction system.

Abstract: Provided is a gas turbine combustor that achieves simplified structure and reduced axial length of the entire device. The combustor includes: a combustion liner forming a combustion chamber; a fuel injector provided at a top portion of the combustion liner; and a housing chamber located upstream of the combustion chamber and housing the fuel injector. The fuel injector includes a fuel supply tube penetrating through the housing chamber and configured to supply fuel to the combustion chamber, and a guide member provided on outer side of a downstream portion of the fuel supply tube for allowing air to pass therethrough. The fuel supply tube has, in the downstream portion, a fuel injection hole for injecting fuel to the air passing through the guide member, so as to mix the fuel with the air. The guide member supplies the air and the fuel to the combustion chamber.

Abstract: A combustor and a gas turbine capable of uniformly supplying air into a burner are provided. The combustor may include a burner including a tubular nozzle casing, a head plate coupled to an end of the nozzle casing, and a plurality of nozzles to inject fuel and air, and a duct assembly coupled to the burner, a mixture of the fuel and the air being burned in the duct assembly to produce combustion gas. Each of the nozzles may include outer nozzles and an inner nozzle installed inside the outer nozzles, each of the outer nozzles may include a nozzle tube configured to provide a channel through which air and fuel flow and a nozzle shroud configured to surround the nozzle tube, and a flow distribution member may be installed between the head plate and the nozzle shroud to distribute a flow rate of air introduced into the outer nozzle.

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

Abstract: A combustor includes a fuel supply unit defining on a radially inner side of an axis an inner peripheral side space into which inert gas is introduced and which is configured to supply the inert gas to a combustion cylinder, and defining on a radially outer side an outer peripheral side space into which the inert gas is introduced and which is configured to supply the inert gas to the combustion cylinder; an inner peripheral side oxygen supply unit that is configured to supply oxygen to the inner peripheral side space; an outer peripheral side oxygen supply unit that is configured to supply oxygen to the outer peripheral side space; and an adjustment unit that is configured to adjust the relative amounts of the oxygen supplied by the inner peripheral side oxygen supply unit and the oxygen supplied by the outer peripheral side oxygen supply unit.

Abstract: Fuel injectors, combustors, and methods of fabricating a fuel injector are provided. A fuel injector includes a forward end wall and an aft end wall disposed oppositely from one another. The fuel injector also includes side walls that extend between the forward end wall and the aft end wall. The forward end wall and the aft end wall are arcuate. The forward end wall, the aft end wall, and the side walls collectively define an opening for passage of air. The fuel injector further includes at least one fuel injection member disposed within the opening and extending between the forward end wall and the aft end wall.

Abstract: A method for operating a burner arrangement of a heat engine, particularly a gas turbine, having a plurality of burners, each having at least one pilot burner and main burner, in which method, on the basis of a preset operation of the heat engine, the total quantity of fuel supplied to the burners is maintained substantially constant in a load-controlled manner: in a first group of burners, for each burner, both the pilot burner as well as the main burner are supplied with fuel; in a second group of burners, the fuel supply to the main burners is interrupted, while the pilot burners continue to be operated; and the fuel quantity remaining as a result of the interruption of the fuel supply to the main burners of the second group is redistributed to the still active main burners of the first group. CO emissions are reduced as a result.

Abstract: A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle, a height, and a base width, where the base width is a function of the height and where the turbulators are spaced an axial distance apart that is a function of the turbulator height.

Abstract: A combustion device includes an ammonia supply unit supplying primary reduction ammonia as a nitrogen oxide reducing agent into a combustor and mixing secondary reduction ammonia with combustion exhaust gas discharged from the combustor to reduce nitrogen oxide contained in the combustion exhaust gas and a controller configured to control at least one of the amount of supply of the primary reduction ammonia and the amount of mixing of the secondary reduction ammonia with the combustion exhaust gas in accordance with concentrations of residual nitrogen oxide and residual ammonia contained in the combustion exhaust gas after being discharged from the combustor.

Abstract: A fuel injector comprising a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector, a splitter arranged between the first air swirler passage and the second air swirler passage and comprising a first splitter surface having a first divergent portion which is divergent in the downstream direction, a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction, a third splitter surface located radially inward of the first and second splitter surface, and a first connecting surface extending between the second and third splitter surfaces, wherein a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity.

Abstract: A nacelle comprising a fixed structure with a fixed cowl and a duct, a mobile assembly with a chassis forming a frame and a mobile cowl, the chassis being mobile, relative to the fixed structure, in translation between an advanced position and a retracted position to open an opening through the frame between the duct and the outside. The mobile assembly comprises at least one threaded rod parallel to the direction of displacement and fixed to the chassis through the frame. The fixed structure comprises an outer, an inner, and at least one intermediate box fixed to the inner box and to the outer box. For each threaded rod, the fixed structure comprises a motorized ball nut which meshes with the threaded rod, and an actuator which turns the ball nut and is fixed to at least one box from among the outer, the inner, or the intermediate box.