Patent application number | Description | Published |
20090260368 | METHOD FOR OPERATING A GAS TURBINE - A method for operating a gas turbine ( | 10-22-2009 |
20110139541 | METHOD FOR ADJUSTING A HELMHOLTZ RESONATOR AND AN ADJUSTABLE HELMHOLTZ RESONATOR - In a method for adjusting a Helmholtz resonator ( | 06-16-2011 |
20110289898 | COMBINED CYCLE POWER PLANT WITH FLUE GAS RECIRCULATION - An exemplary system method for the operation of a CCP P with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases is disclosed. The flue gas recirculation rate (rFRG) is controlled as function of the combustion pressure and/or the hot gas temperature. Operability is enhanced by admixing of oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustion. | 12-01-2011 |
20110289899 | COMBINED CYCLE POWER PLANT WITH FLUE GAS RECIRCULATION - An exemplary method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases as well as a plant designed to operate is disclosed. To allow a high flue gas recirculation ration (rFRG) an imposed combustion inhomogeneity ratio (ri) is used for flame stabilization. The imposed combustion inhomogeneity ratio (ri) is controlled as function of the flue gas recirculation rate (rFRG) and/or combustion pressure. Oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustor is admixed to enhance operatability. | 12-01-2011 |
20140013759 | PREMIX BURNER OF THE MULTI-CONE TYPE FOR A GAS TURBINE - The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction. | 01-16-2014 |
20140033728 | GAS TURBINE ASSEMBLY AND CORRESPONDING OPERATING METHOD - The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring. | 02-06-2014 |
20140109591 | DAMPER ARRANGEMENT FOR REDUCING COMBUSTION-CHAMBER PULSATION - The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor. | 04-24-2014 |
Patent application number | Description | Published |
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 |
20150059345 | SIMULTANEOUS BROADBAND DAMPING AT MULTIPLE LOCATIONS IN A COMBUSTION CHAMBER - The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes. | 03-05-2015 |