| Patent application number | Description | Published |
|---|
| 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 |
| 20090068609 | Burner Arrangement - A burner arrangement is disclosed with a conical swirler in the form of a double cone which is arranged concentric to a burner axis and which encloses a swirl chamber, and with a central fuel lance which lies in the burner axis and projects from the cone point of the swirler into the swirl chamber, wherein a first stage is provided for injecting premix fuel, in which the premix fuel is injected radially outwards into the swirl chamber through injection openings which are arranged on the fuel lance, and wherein a second stage is provided for injecting premix fuel, in which the premix fuel is injected into an air flow, which is guided in the double cone, through injection openings in the double cone. With such a burner arrangement, the gas pressure which is required in the first stage is reduced by the entire premix fuel being injected into the swirl chamber in the first stage through two oppositely-disposed injection openings with increased opening diameter. | 03-12-2009 |
| 20090094960 | METHOD FOR OPERATING A GAS TURBINE, METHOD OF OPERATION OF A COMBINED CYCLE POWER PLANT, AND COMBINED CYCLE POWER PLANT - In a method for operating a gas turbine (GT) with sequential combustion, which has at least one compressor ( | 04-16-2009 |
| 20090123882 | METHOD FOR OPERATING A BURNER - A method and an apparatus are provided for the combustion of gaseous fuel containing hydrogen or consisting of hydrogen, with a burner which provides a swirl generator, into which liquid fuel is fed centrally along a burner axis, at the same time forming a conically shaped liquid fuel column which is surrounded by a rotating combustion air stream which flows tangentially into the swirl generator and into which, additionally, a gaseous and/or liquid fuel is injected so as to form a fuel/air swirl flow which is transferred downstream of the swirl generator, along a transitional portion, into a mixing zone following the transitional portion downstream and which is ignited and burnt in a combustion chamber following downstream, at the same time forming a backflow zone. | 05-14-2009 |
| 20090260368 | METHOD FOR OPERATING A GAS TURBINE - A method for operating a gas turbine ( | 10-22-2009 |
| 20090282830 | COMBUSTOR WITH REDUCED CARBON MONOXIDE EMISSIONS - A combustor arrangement for a gas turbine engine ( | 11-19-2009 |
| 20090282831 | METHOD FOR REDUCING EMISSIONS FROM A COMBUSTOR - A modification method for reducing emissions from an annular shaped combustor of a gas turbine plant, having uniformly spaced circumferentially mounted premix burners ( | 11-19-2009 |
| 20100077720 | METHODS OF REDUCING EMISSIONS FOR A SEQUENTIAL COMBUSTION GAS TURBINE AND COMBUSTOR FOR A GAS TURBINE - In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor ( | 04-01-2010 |
| 20100077756 | FUEL LANCE FOR A GAS TURBINE ENGINE - A fuel lance ( | 04-01-2010 |
| 20100146983 | BURNER FOR A COMBUSTOR OF A TURBOGROUP | 06-17-2010 |
| 20100175382 | GAS TURBINE BURNER - The burner ( | 07-15-2010 |
| 20100192591 | BURNER FOR A GAS TURBINE AND METHOD FOR FEEDING A GASEOUS FUEL IN A BURNER | 08-05-2010 |
| 20100229570 | BURNER FOR A GAS TURBINE AND METHOD FOR LOCALLY COOLING A HOT GASES FLOW PASSING THROUGH A BURNER - The burner ( | 09-16-2010 |
| 20100236246 | BURNER OF A GAS TURBINE - An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052. | 09-23-2010 |
| 20100266970 | METHOD AND DEVICE FOR COMBUSTING HYDROGEN IN A PREMIX BURNER - A device for combusting fuel which contains or consists of hydrogen, is described, with a burner provided with a swirl generator and also a feeder for feeding fuel and a feeder for feeding combustion air into the swirl generator. A first feeder, for feeding liquid fuel along a burner axis, and a second feeder for feeding liquid fuel or gaseous fuel along air inlet slots which are tangentially delimited by the swirl generator, with a transition section connected downstream to the swirl generator, and with a mixer tube connected downstream to the transition section and with a changeable flow cross-sectional transition leads into a combustion chamber are provided. Along the transition section, a third feeder for feeding fuel which contains or consists of hydrogen, and also a fourth feeder for the selective feed of fuel which contains or consists of hydrogen, or of the gaseous fuel are also provided. | 10-21-2010 |
| 20100273117 | PREMIX BURNER FOR A GAS TURBINE - A premix burner is provided, with a swirl generator and a downstream mixer tube for combusting gaseous and liquid fuel which during entry of combustion air is introduced into the burner interior space of the swirl generator and/or is introduced into the burner interior of the swirl generator on a burner axis, and also with a fuel lance which is arranged on the burner axis. The premix burner, in the transition section from the swirl generator to the mixer tube, includes at least one additional feed for introducing gaseous and/or liquid premix fuel from the wall region into the burner interior space of the mixer tube. | 10-28-2010 |
| 20100300109 | FUEL INJECTION METHOD - A method is provided for fuel injection in a sequential combustion system comprising a first combustion chamber and downstream thereof a second combustion chamber, in between which at least one vortex generator is located, as well as a premixing chamber having a longitudinal axis downstream of the vortex generator, and a fuel lance having a vertical portion and a horizontal portion, being located within said premixing chamber. The fuel injected is an MBtu-fuel. In said premixing chamber the fuel and a gas contained in an oxidizing stream coming from the first combustion chamber are premixed to a combustible mixture. The fuel is injected in such a way that the residence time of the fuel in the premixing chamber is reduced in comparison with a radial injection of the fuel from the horizontal portion of the fuel lance. | 12-02-2010 |
| 20100330282 | SLURRY FORMULATION FOR THE PRODUCTION OF THERMAL BARRIER COATINGS - A slurry formulation for production of a patch or a strip of a thermal barrier coating includes 20-60 dry weight percent of alkali metal silicate binder, 40-80 dry weight percent of ceramic fillers including at least one ceramic filler selected from the group consisting of yttria-stabilized zirconia and magnesia, 0-20 dry weight percent of additives, wherein the dry weight percent of the alkali metal silicate binder, the ceramic fillers and the additives add up to 100%, and one of a solvent and suspension agent. | 12-30-2010 |
| 20110027732 | BURNER OF A GAS TURBINE - The burner of a gas turbine includes two or more part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein. A lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber is also provided. A portion of the nozzle facing the cone shaped chamber is divergent in shape. A diffuser angle (α) between the wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5°. A diverging portion of the nozzle has a diffuser length to nozzle diameter ratio comprised between 2-6. The nozzle diameter is the smaller diameter of the diverging portion. | 02-03-2011 |
| 20110079014 | BURNER ARRANGEMENT, AND USE OF SUCH A BURNER ARRANGEMENT - A burner arrangement includes a tubular mixing tube extending along an axis and configured to mix fuel and air, the mixing tube opening into a combustion chamber in a direction of flow; and a film air ring disposed in the mixing tube and arranged concentrically to the axis, the film air ring configured to prevent a backfiring of the fuel disposed in the mixing tube and to generate or reinforce an air film near the wall, wherein the film air ring has at least one annular gap concentric to the axis and configured to inject air. | 04-07-2011 |
