Patent application number | Description | Published |
20090260368 | METHOD FOR OPERATING A GAS TURBINE - A method for operating a gas turbine ( | 10-22-2009 |
20120090326 | POWER PLANT - A power plant includes a gas turbine unit adapted to feed flue gases into a diverter where they are divided into a recirculated flow that is fed into a mixer together with fresh air to form a mixture that is fed to a gas turbine unit compressor inlet, and a discharged flow, that is fed into a CO | 04-19-2012 |
20120090327 | POWER PLANT AND METHOD FOR ITS OPERATION - The power plant includes a gas turbine unit adapted to feed flue gases into a diverter where they are divided into a recirculated flow and a discharged flow. The recirculated flow is fed into a mixer together with fresh air to form a mixture that is fed to the gas turbine unit. The gas turbine unit includes a combustion chamber where a fuel is burnt together with the mixture. A control unit is provided, that is supplied with information regarding the fuel C2+ and/or H | 04-19-2012 |
20120090328 | POWER PLANT - A power plant includes a gas turbine unit adapted to feed whose flue gases into a boiler of a steam turbine unit, to be then diverted into a recirculated flow and discharged flow. The recirculated flow is mixed with fresh air forming a mixture that is fed into a gas turbine unit compressor. The discharged flow is fed into a CO | 04-19-2012 |
20120186268 | CONTROL OF THE GAS COMPOSITION IN A GAS TURBINE POWER PLANT WITH EXHAUST GAS RECIRCULATION - A method is provided for operating a gas turbine power plant with exhaust gas recirculation, in which, based upon the operating state of the gas turbine a setpoint concentration of at least one constituent in an exhaust gas flow and/or in the intake flow of the gas turbine after adding the recirculated exhaust gases is determined. The actual concentration of the at least one constituent in the exhaust gas flow and/or in the intake flow is measured and a control element for controlling the recirculation flow is controlled based upon the setpoint/actual deviation. Also provided is a gas turbine power plant with exhaust gas recirculation and includes a controller, in which a setpoint concentration of at least one constituent in an exhaust gas flow or in the intake flow of the gas turbine is determined, and a measuring instrument for measuring the actual concentration of the at least one constituent. | 07-26-2012 |
20120240590 | GAS TURBINE POWER PLANT WITH FLUE GAS RECIRCULATION AND OXYGEN-DEPLETED COOLING GAS - A method is disclosed for operating a gas turbine power plant having a gas turbine, a heat recovery steam generator and an flue gas splitter which splits flue gases into a first flue gas flow for recirculation into an inlet flow of the gas turbine and into a second flue gas flow for discharge to an environment. An oxygen-depleted gas can be used in an open cooling system for cooling hot gas parts of the gas turbine. A split compressor intake can be provided for separate feed of recirculated flue gas and fresh air into a compressor intake. Compressor blades can include a separating band which blocks intermixing of recirculated flue gas and fresh air during compression. | 09-27-2012 |
20120291445 | METHOD FOR OPERATING A GAS TURBINE POWER PLANT WITH EXHAUST GAS RECIRCULATION - An exemplary method is disclosed for operating a gas turbine power plant with exhaust gas recirculation, in which the exhaust gas recirculation is, for example, disengaged during starting and shutting down of the gas turbine, and in which the engaging or disengaging of the exhaust gas recirculation can be carried out in dependence upon an operating state of the gas turbine. An exemplary gas turbine power plant with exhaust gas recirculation is also disclosed which can include a control element, the closing speed of which is such that the control element can be closed within a time which is less than a time for exhaust gases to flow from the turbine through an HRSG. | 11-22-2012 |
20130086883 | METHOD FOR OPERATING A GAS TURBINE POWER PLANT WITH FLUE GAS RECIRCULATION - A method and system are disclosed for operating a gas turbine power plant with flue gas recirculation, in which variable compressor inlet guide vanes are controlled as a function of flue gas recirculation ratio and/or as a function of a process parameter which is indicative for the flue gas recirculation. A controller setpoint position of the variable compressor inlet guide vanes can be controlled as a function of a position of a control element for controlling flue gas recirculation flow. | 04-11-2013 |
20130305732 | MIXING ELEMENT FOR GAS TURBINE UNITS WITH FLUE GAS RECIRCULATION - The invention pertains to fluegas recirculation in gas turbines, and specifically to an intake section upstream of the inlet of a compressor of a gas turbine unit with fluegas recirculation. The intake section includes at least one section with a flow path defined by sidewalls in which the fresh airflow of the intake air is flowing along a principal airflow direction, including at least one mixing duct extending into the flow path from at least one sidewall. The mixing duct includes an intake at the at least one sidewall for receiving recirculated fluegas, as well as including at least one outlet opening distanced from said sidewall for blowing recirculated fluegas out of the mixing duct into the airflow. | 11-21-2013 |
20140360154 | GAS TURBINE PLANT HAVING EXHAUST GAS RECIRCULATION - The invention relates to a gas turbine plant, including a gas turbine device, which has a compressor and at least one burner and at least one gas turbine, a waste heat boiler assembly, which has a boiler inlet side connected to a turbine outlet and a first boiler outlet connected to a flue and a second boiler outlet, and an exhaust gas recirculation, which connects the second boiler outlet to a compressor inlet. A simplified structure can be achieved in that the waste heat boiler assembly has a first boiler exhaust gas path, which is connected to the boiler inlet side and leads to the first boiler outlet, and that the waste heat boiler assembly has a second boiler exhaust gas path, which is connected to the boiler inlet side and leads to the second boiler outlet separately from the first boiler exhaust gas path. | 12-11-2014 |
20140360199 | METHOD OF OPERATING A GAS TURBINE POWER PLANT WITH EXHAUST GAS RECIRCULATION AND CORRESPONDING GAS TURBINE POWER PLANT - The invention relates to a method for operating a gas turbine, in which an oxygen-reduced gas and fresh air are delivered to a compressor of the gas turbine in a radially staged manner, the fresh air being delivered via an outer sector of the inlet cross section in relation to the axis of rotation of the compressor, and the oxygen-reduced gas being delivered via an inner sector of the inlet cross section in relation to the axis of rotation of the compressor. | 12-11-2014 |
20140360200 | GAS TURBINE POWER PLANT WITH EXHAUST GAS RECIRCULATION - What is described is a method for operating a gas turbine power plant, in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet. What is described, further, is a gas turbine power plant with a gas turbine, the compressor inlet of which is divided into two sectors which the flow duct of the compressor adjoins, a feeder for fresh air being connected to the first sector and a recirculation line for recirculating the first exhaust gas substream being connected to the second sector, and the second sector reaching so close to the compressor that, when the gas turbine is in operation, the static pressure at the outlet of the second sector is so low that the difference between total pressure and static pressure is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet. | 12-11-2014 |
20150047314 | INTAKE ARRANGEMENT IN GAS TURBINE POWER PLANT - An intake arrangement for a compressor in a gas turbine power plant includes at least a passageway having an elongated portion, and a circular portion at an end of the elongated portion. The circular portion may be arranged in proximity to the compressor at around a compressor inlet. The passageway may be divided at least circumferentially and radially across the entire elongated portion and at least partially across the circular portion to configure a plurality of flue gas and air inlet segments for respectively conveying flue gas and air streams therethrough. The flue and air gas streams from each of the respective plurality of flue gas and air inlet segments, converge to be blended into a target mass stream for being conveyed into the compressor. | 02-19-2015 |
20150050140 | INTAKE ARRANGEMENT IN GAS TURBINE POWER PLANT - An improved intake arrangement, for a compressor having a compressor blading, includes a manifold divided by a barrier into two sections, to convey, from one section, a flue gas stream, and, from other section, an air stream. Further, the intake arrangement includes a converging section configured to the manifold and extends convergingly to the compressor defining an inlet to the compressor blading. The converging section includes inner and outer ring members disposed coaxially to each other, between which there extends, coaxially and convergingly, the barrier to at least up to a certain distance within the converging section, defining a converging nozzle therebetween. The converging nozzle includes a mixing feature adapted to enhance mixing of the flue gas and air streams. | 02-19-2015 |
Patent application number | Description | Published |
20090042154 | BURNER FOR A COMBUSTOR OF A TURBOGROUP - A burner for a combustor of a turbogroup is provided. The burner includes a burner body, an outlet flange, and a plenum which is exposed, or can be exposed, to admission of cooling medium. In order to improve the cooling of the outlet flange, a flow passage and a supply passage are formed. The flow passage and the supply passage are arranged so that the cooling medium from the plenum enters the flow passage, is transferred from the flow passage into the supply passage, and is discharged from the supply passage through holes into a burner interior. | 02-12-2009 |
20090044539 | FUEL LANCE FOR A GAS TURBINE INSTALLATION AND A METHOD FOR OPERATING A FUEL LANCE - A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance for injecting fuel into the hot gas is arranged. The fuel lance has a lance section which extends in the flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to the lance tip and is injected through first injection openings in the region of the lance tip into the hot gas. The fuel lance is modified for operation with syngas by the first injection openings being arranged directly on the lance tip, and by the first injection openings being oriented so that the fuel jets which emerge from them include an acute angle with the lance axis. | 02-19-2009 |
20100229570 | BURNER FOR A GAS TURBINE AND METHOD FOR LOCALLY COOLING A HOT GASES FLOW PASSING THROUGH A BURNER - The burner ( | 09-16-2010 |
20110150635 | SEAL AND SEAL ARRANGEMENT FOR CONFINING LEAKAGE FLOWS BETWEEN ADJACENT COMPONENTS OF TURBO-MACHINES AND GAS TURBINES - A seal for stemming leakage flows between adjacent components ( | 06-23-2011 |
20110185746 | GAS TURBINE COMBUSTION DEVICE - The combustion device ( | 08-04-2011 |
20110203250 | COMBUSTION DEVICE FOR A GAS TURBINE - A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages | 08-25-2011 |
20110265484 | COMBUSTION DEVICE FOR A GAS TURBINE - A combustion device ( | 11-03-2011 |
20120036824 | REHEAT BURNER - A reheat burner ( | 02-16-2012 |
20120060503 | TRANSITIONAL REGION FOR A COMBUSTION CHAMBER OF A GAS TURBINE - A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform. | 03-15-2012 |
20120260657 | COMBUSTOR OF A GAS TURBINE - An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat. | 10-18-2012 |
20120297777 | REHEAT BURNER INJECTION SYSTEM WITH FUEL LANCES - The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body. | 11-29-2012 |
20120324863 | COOLING SCHEME FOR AN INCREASED GAS TURBINE EFFICIENCY - A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body. | 12-27-2012 |
20140109588 | BURNER FOR A CAN COMBUSTOR - The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile. At least one of the streamlined bodies is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel, wherein at least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor. The invention also relates to a method of using said burner in a gas turbine. | 04-24-2014 |
20140116059 | HOT GAS SEGMENT ARRANGEMENT - A hot gas segment arrangement, especially for a combustion chamber of a gas turbine, that includes at least one hot gas segment, which is removably mounted on a carrier, and is subjected at its outside to hot gas and impingement-cooled at its inside, whereby an impingement plate with a plurality of distributed impingement holes is arranged in a distance at the inside of the impingement plate. A cooling air supply means is provided for loading the impingement plate with pressurized cooling air in order to generate through the impingement holes jets of cooling air, which impinge on the inside of the hot gas segment. The cooling efficiency and lifetime are increased by the impingement plate being part of a closed receptacle, which is supplied with the pressurized cooling air, and by the receptacle with the impingement plate being mounted on the carrier independently of the hot gas segment. | 05-01-2014 |
20140150435 | DAMPING DEVICE FOR A GAS TURBINE COMBUSTOR - The invention relates to a damping device for a gas turbine combustor with significantly reduced cooling air mass flow requirements. The damping device includes a wall with a first inner wall and a second outer wall, arranged in a distance to each other. The inner wall is subjected to high temperatures on a side with a hot gas flow. A plurality of cooling channels extend essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels. Furthermore, the damping device includes a first passage for supplying a cooling medium from a cooling channel into the damping volume and a second passage for connecting the damping volume to the combustion chamber. An end plate, fixed to the inner wall, separates the damping volume from the combustion chamber. | 06-05-2014 |
20140345285 | DAMPER FOR GAS TURBINES - The invention relates to a damper for reducing the pulsations in a combustion chamber of a gas turbine. The damper includes a resonator cavity with an inlet and a neck tube in flow communication with the interior of the combustion chamber and resonator cavity, and a compensation assembly pivotably connected with the neck tube. The compensation assembly is inserted between the resonator cavity and the combustion chamber to permit relative rotation between the combustion chamber and the resonator cavity. With the damper according to the present invention, by way of providing the compensation assembly, it is assured the relative rotation between the combustion chamber and the resonator cavity is compensated, hence operation life is elongated. | 11-27-2014 |
20150047313 | COMBUSTOR OF A GAS TURBINE WITH PRESSURE DROP OPTIMIZED LINER COOLING - A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed. | 02-19-2015 |
20150047364 | BURNER ARRANGEMENT AND METHOD FOR OPERATING A BURNER ARRANGEMENT - The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper. | 02-19-2015 |
20150075168 | COMBUSTION CHAMBER SEAL SEGMENTS EQUIPPED WIHT DAMPING DEVICES - A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels. | 03-19-2015 |