Patent application number | Description | Published |
20090077975 | Heat shield element for lining a combustion chamber wall, combustion chamber and gas turbine - The invention relates to a heat shield element for lining a combustion chamber wall, to a combustion chamber and to a gas turbine. The heat shield element comprises a hot side that can be exposed to a hot medium, a wall side opposite said hot side, and a peripheral side adjoining the hot side and the wall side and having a peripheral side surface. Relief slots are introduced into the material in an area of the heat shield element that is susceptible to material cracks induced by thermal stress, thereby limiting crack propagation. | 03-26-2009 |
20100043440 | Gas Turbine Burner and Method of Operating a Gas Turbine Burner - The invention is based on a gas turbine burner comprising a combustion zone for burning a mixture consisting of combustion exhaust gas to which fuel gas is added, and comprising a fuel intermixing arrangement having a fuel nozzle for spraying the fuel gas into the combustion exhaust gas. In order to achieve low-pollutant and uniform combustion, it is proposed that the fuel intermixing arrangement be designed for spraying the fuel gas into the combustion exhaust gas at at least 0.2 times the speed of sound. | 02-25-2010 |
20100180598 | Burner and method for operating a burner - A method for operating a burner including a burner outlet opening with at least two sectors, each sector is assigned at least one fuel nozzle, is provided. The method is characterized in that fuel is supplied separately to the fuel nozzles of different sectors. Also described is a burner which includes at least two sectors wherein each sector is assigned at least one fuel nozzle. The burner includes at least two separate fuel supply lines and a device for adjusting the fuel mass flow which flows through the respective fuel supply line. The fuel supply lines supply fuel to the fuel nozzles of different sectors. Also described is a gas turbine which is fitted with at least one burner. | 07-22-2010 |
20100213645 | Heat Shield Element, Method and Mold for the Production Thereof, Hot-Gas Lining and Combustion Chamber - There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot side to the cold side and a material volume which is defined by the hot side, the cold side and the peripheral sides, wherein the material volume comprises at least two material areas which are made of different materials. The materials are different from each other at least in respect of their resistance and/or thermal expansion coefficient. | 08-26-2010 |
20100251687 | GAS TURBINE: SEAL BETWEEN ADJACENT CAN ANNULAR COMBUSTORS - The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate. | 10-07-2010 |
20110024517 | Swirl spraying nozzle for sprayng liquid fuel, and method of producing same, and a nozzle assembly for a burner with the swirl spraying nozzle - A swirl spraying nozzle for spraying liquid fuel is provided. The swirl spraying nozzle includes a nozzle body including a hollow cylinder with a base terminating the hollow cylinder on one side and with a head terminating the hollow cylinder on the other side such that a swirl chamber is formed in the nozzle body. An admission hole is provided in the hollow cylinder in the vicinity of the base and is arranged in a plane perpendicular to the longitudinal axis of the hollow cylinder. The admission hole is positioned at an angle in the circumferential direction of the hollow cylinder. An outlet hole is provided in the head on the longitudinal axis of the hollow cylinder such that a liquid can flow tangentially through the admission hole with a swirling action into the swirl chamber and can flow out axially from the swirl chamber through the outlet opening. | 02-03-2011 |
20110188999 | Axial turbine for a gas turbine with limited play between blades and housing - An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine. | 08-04-2011 |
20120228468 | Heat Shield Element, Method and Mold for the Production Thereof, Hot-Gas Lining and Combustion Chamber - There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot side to the cold side and a material volume which is defined by the hot side, the cold side and the peripheral sides, wherein the material volume comprises at least two material areas which are made of different materials. The materials are different from each other at least in respect of their resistance and/or thermal expansion coefficient. A mold to make the heat shield element is also provided. | 09-13-2012 |
20140345290 | METHOD FOR STABILIZING A GRID FREQUENCY WITH A GAS TURBINE IN MIXED FUEL OPERATION - A method for stabilising a network frequency with a gas turbine that can be operated using syngas and an additional fuel is provided. The mass-flow of the additional fuel, supplied to operate the gas turbine, can be increased more quickly than that of the syngas and, in order to stabilise a network frequency, a ratio of the mass-flow of syngas to that of the additional fuel, for operating said gas turbine, is modified by the mass-flow of said additional fuel being modified while the mass-flow of the syngas remains the same. | 11-27-2014 |