Patent application number | Description | Published |
20100124502 | ROTOR BLADE ARRANGEMENT AND GAS TURBINE - A rotor blade arrangement ( | 05-20-2010 |
20100150727 | ROTOR BLADE FOR A GAS TURBINE - A rotor blade ( | 06-17-2010 |
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 |
20110110785 | ROTOR FOR AN AXIAL-THROUGHFLOW TURBOMACHINE AND MOVING BLADE FOR SUCH A ROTOR - A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction. | 05-12-2011 |
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 |
20120163995 | TURBINE BLADE - A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals. | 06-28-2012 |
20130058785 | VIBRATION DAMPER FOR ROTATING PARTS - A rotating element for a rotating machine, in particular for a turbine machine, is provided with a vibration damper for vibrations of the rotating element during operation of the machine. The vibration damper includes a closed cavity in the body of the rotating element. In the closed cavity there is located a movable solid damping body as well as a damping medium. The damping medium is based on a metal which is in liquid state at the operation temperature where damping is desired. It furthermore relates to turbo machines equipped with such rotating elements as well as to uses of liquid metal for such vibration dampers. | 03-07-2013 |
20130058788 | LIGHT WEIGHT SHROUD FIN FOR A ROTOR BLADE - A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge. | 03-07-2013 |
20140030077 | STATIONARY GAS TURBINE ARRANGEMENT AND METHOD FOR PERFORMING MAINTENANCE WORK - The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means. | 01-30-2014 |
20140234088 | MODULAR BLADE OR VANE FOR A GAS TURBINE AND GAS TURBINE WITH SUCH A BLADE OR VANE - The invention relates to a modular blade or vane for a gas turbine, which includes the modular components of a platform element with a planar or contoured surface defining a platform level and a through-opening therein, and an airfoil, extending through the platform element. The airfoil includes a load carrying structure extending along a longitudinal axis of the airfoil, having a root portion for fastening on a blade or vane carrier of the gas turbine, having a tip portion, and having at least one interior passage, extending from the root portion to the tip portion of the airfoil. An aerodynamically shaped shell extends in a distance over the carrying structure and defining the outer contour of the airfoil. A longitudinally extending gap, is disposed between the carrying structure and the shell. A number of through-holes in the carrying structure direct a cooling medium from the interior passage into the gap. The shell is integrally joined to said carrying structure by a first joint in a region below the platform level of the platform element. The shell is joined to the carrying structure by at least one additional joint, wherein said at least one additional joint is a form-fit joint, allowing relative movement in longitudinal direction between shell and carrying structure. | 08-21-2014 |
20140242408 | METHOD FOR MANUFACTURING A METAL-CERAMIC COMPOSITE STRUCTURE AND METAL-CERAMIC COMPOSITE STRUCTURE - The invention relates to a method for manufacturing a metal-ceramic composite structure intended to be exposed to high temperatures. The composite structure includes a base metal structure or component, which is on at least one side covered and permanently joined with one or more ceramic tiles. | 08-28-2014 |
20140328672 | STATOR COMPONENT WITH SEGMENTED INNER RING FOR A TURBOMACHINE - A stator component of a turbomachine is composed substantially of at least one axially extending outer ring ( | 11-06-2014 |
20140334914 | COMPONENT FOR A THERMAL MACHINE, IN PARTICULAR A GAS TURBINE - The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge. | 11-13-2014 |
20150017007 | TURBINE BLADE OR VANE - The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state. | 01-15-2015 |