Patent application number | Description | Published |
20100119371 | SHIPLAP ARRANGEMENT - An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal. | 05-13-2010 |
20110058953 | TURBINE BLADE - A turbine blade is provided having an airfoil and a platform manufactured in two separate pieces, which are joined together. The blade includes a seal, which is a mechanically decoupled seal, interposed between the airfoil and platform in a position closer to a hot gases path than a joint. | 03-10-2011 |
20110070077 | GAS TURBINE - A gas turbine ( | 03-24-2011 |
20110135497 | TURBINE BLADE - A blade is provided and includes a platform and a root configured to be connected to a blade carrier. Airfoil portions extend from opposite sides of the platform. Each airfoil portion defines an operating surface being the surface facing the other airfoil portion. An operating surface of one of the airfoil portions defines a suction side and the other operating surface of the other airfoil portion defines a pressure side. | 06-09-2011 |
20120156035 | BLADE ARRANGEMENT FOR A GAS TURBINE AND METHOD FOR OPERATING SUCH A BLADE ARRANGEMENT - A blade arrangement is provided for a gas turbine, in which blade leaves, having a leading edge and a trailing edge and also a pressure side and a suction side, are assembled sealingly with platforms configured as separate components. A peripheral sealing arrangement is provided between the blade leaves and the associated platforms, which seals off an interspace between the blade leaves and platforms against hot gas flowing around the blade leaves. A directed site-dependent supply of cooling air for purging the sealing arrangement is provided on a side of the sealing arrangement which faces away from the hot gas. A method of operating the above blade arrangement is also provided. The method includes supplying cooling air for purging the sealing arrangement at a pressure which decreases from the leading edge of the blade leaves to the trailing edge. | 06-21-2012 |
20130067933 | GAS TURBINE - A gas turbine is provided and includes a compressor, which via an air intake inducts and compresses air; a combustion chamber, in which a fuel is combusted using the compressed air, producing a hot gas; and a turbine, equipped with turbine blades, in which the hot gas is expanded, performing work. A first device is provided in order to cool turbine blades with compressed cooling air. The first device includes at least one separate compressor stage which produces compressed cooling air independently of the compressor. | 03-21-2013 |
20140086743 | METHOD AND COOLING SYSTEM FOR COOLING BLADES OF AT LEAST ONE BLADE ROW IN A ROTARY FLOW MACHINE - A method and a cooling system for cooling blades of at least one blade row in a rotary flow machine includes an axial flow channel which is radially limited on the inside by a rotor unit and at the outside by at least one stationary component, the blades are arranged at the rotary unit and provide a shrouded blade tip facing radially to said stationary component. Pressurized cooling air is fed through from radially outside towards the tip of each of said blades in the at least one blade row, and the pressurized cooling air enters the blades through at least one opening at the shrouded blades' tip. | 03-27-2014 |
20140112798 | GAS TURBINE AND TURBINE BLADE FOR SUCH A GAS TURBINE - A gas turbine includes a rotor concentrically surrounded by a casing, with an annular hot gas channel axially extending between the rotor and the casing. The rotor is equipped with a plurality of blades, which are arranged on the rotor in an annular fashion. Each of the blades is mounted with a root in a respective axial slot on a rim of the rotor radially extending with an airfoil into said hot gas channel and adjoining with an axially oriented root surface to an annular rim cavity. Cooling means are provided at the root of each of said blades to receive cooling air being injected into said rim cavity through stationary injecting means. An optimized cooling is achieved by providing the root surface to be an essentially plane surface and the cooling means including a scoop for capturing and redirecting at least part of the injected cooling air, which scoop is designed as a recess with respect to the root surface. | 04-24-2014 |
20140191476 | LABYRINTH SEAL - A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition. | 07-10-2014 |
20150037167 | TURBINE BLADE AND TURBINE WITH IMPROVED SEALING - The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine. | 02-05-2015 |
20150050125 | FLUID SEAL ARRANGEMENT AND METHOD FOR CONSTRICTING A LEAKAGE FLOWTHROUGH A LEAKAGE GAP - The invention refers to a fluid seal arrangement for constricting a leakage flow directed through a leakage gap bordered by a rotational and a stationary component including at least one nozzle opening in the rotating and/or stationary component facing towards the rotating or stationary component of an opposite side of the leakage gap respectively in order for injecting a liquid or gaseous fluid flow through the nozzle opening into the leakage gap. The at least one nozzle opening is fluidly connected to a cooling channel inside said rotating and/or stationary component, so that said fluid flow emanating at the nozzle opening consists of a cooling fluid of the rotating and/or stationary component exclusively. | 02-19-2015 |