Patent application number | Description | Published |
20100124493 | MULTI-VANE SEGMENT DESIGN AND CASTING METHOD - Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud. | 05-20-2010 |
20100166563 | METHOD FOR IMPROVING THE SEALING ON ROTOR ARRANGEMENTS - A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described. | 07-01-2010 |
20110016875 | GUIDE VANE HAVING HOOKED FASTENER FOR A GAS TURBINE - A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer platform, the inner side of which is exposed to the hot gas which flows through the gas turbine, and on which provision is made for a hook-like fastening element, projecting outwards in the region of the trailing edge, for fastening the stator vane on a casing of the gas turbine, which fastening element, on its side facing the trailing edge, has a locating slot above the trailing edge for the fixing of a heat shield which adjoins the outer platform of the stator vane in the flow direction of the hot gas. With such a stator vane, the service life can be extended by provision being made on the outer platform of the stator vane between the locating slot and the trailing edge of structure for reducing the thermal and mechanical stresses in the region of the transition between trailing edge and outer platform. | 01-27-2011 |
20110058957 | BLADE FOR A GAS TURBINE - A blade is provided for a gas turbine, especially for the low-pressure turbine of a gas turbine with sequential combustion, and is produced in accordance with a casting process and has a blade airfoil which extends in the radial direction between an inner platform and an outer platform, and in the interior of which extends a cooling passage, bypassing the platforms, and through which flows a cooling medium, especially cooling air, for cooling the blade. In the outer and/or inner platform there are core outlet openings which arise from the use of a casting core and which connect the cooling passage to the outside space and are sealed off by means of a sealing element. Optimum cooling is ensured by the sealing elements being formed and inserted into the core outlet openings so that they align with the wall surface of the cooling passage in a flush manner. | 03-10-2011 |
20110189002 | TURBINE GUIDE VANE - A turbine guide vane ( | 08-04-2011 |
20110243756 | METHOD FOR PRODUCING A BLADE BY CASTING AND BLADE FOR A GAS TURBINE - A method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a single cooling air channel running in the blade longitudinal direction from the blade root to the blade tip. The method includes, during the casting of the blade, the blade material being fed exclusively from the blade root into the mold provided therefor, and the cooling air channel is formed during the casting of the blade by using a single core body, which is provided, at the blade tip, with a local casting cross section increasing element. | 10-06-2011 |
20110286834 | GUIDE VANE FOR A GAS TURBINE - A guide vane is provided for a gas turbine and has an airfoil extending in the radial direction between an inner platform and an outer platform. The airfoil extends transversely to the direction of the hot gas flow between a leading edge and a trailing edge and has a pressure side and a suction side. A cooling slot running parallel to the trailing edge is provided on the pressure side in front of the trailing edge, a cooling medium can exit through the cooling slot from the guide vane over the entire length of the guide vane and can cool the trailing edge of the guide vane. In such a guide vane, the service life is extended by a thermal stress reducing element provided on the inner platform below the trailing edge and the cooling slot. | 11-24-2011 |
20110286849 | BLADE FOR A GAS TURBINE - A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width. | 11-24-2011 |
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 |
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 |
Patent application number | Description | Published |
20100276727 | REVERSE-CONDUCTING SEMICONDUCTOR DEVICE - A reverse-conducting semiconductor device is disclosed with an electrically active region, which includes a freewheeling diode and an insulated gate bipolar transistor on a common wafer. Part of the wafer forms a base layer with a base layer thickness. A first layer of a first conductivity type with at least one first region and a second layer of a second conductivity type with at least one second and third region are alternately arranged on the collector side. Each region has a region area with a region width surrounded by a region border. The RC-IGBT can be configured such that the following exemplary geometrical rules are fulfilled: each third region area is an area, in which any two first regions have a distance bigger (i.e., larger) than two times the base layer thickness; the at least one second region is that part of the second layer, which is not the at least one third region; the at least one third region is arranged in the central part of the active region in such a way that there is a minimum distance between the third region border to the active region border of at least once the base layer thickness; the sum of the areas of the at least one third region is between 10 and 30% of the active region; and each first region width is smaller than the base layer thickness. | 11-04-2010 |
20130026537 | POWER SEMICONDUCTOR DEVICE - A power semiconductor device is disclosed with layers of different conductivity types between an emitter electrode on an emitter side and a collector electrode on a collector side. The device can include a drift layer, a first base layer in direct electrical contact to the emitter electrode, a first source region embedded into the first base layer which contacts the emitter electrode and has a higher doping concentration than the drift layer, a first gate electrode in a same plane and lateral to the first base layer, a second base layer in the same plane and lateral to the first base layer, a second gate electrode on top of the emitter side, and a second source region electrically insulated from the second base layer, the second source region and the drift layer by a second insulating layer. | 01-31-2013 |
20150028382 | INSULATED GATE BIPOLAR TRANSISTOR WITH HIGH EMITTER GATE CAPACITANCE - An IGBT is disclosed with a high emitter-gate capacitance, wherein an active cell region can include plural emitter and gate regions. A termination edge region can include a varied lateral doping region VLD. Each gate polysilicon layer can be arranged at a surface of the semiconductor substrate in the gate regions, separated from the semiconductor substrate by a first insulating layer. A first SIPOS layer and a covering second insulating layer overlie at least portions of the gate polysilicon layer. In a central area, the gate polysilicon layer is in electrical contact with the overlying first SIPOS layer whereas, in a peripheral area, the gate polysilicon layer is electrically separated from the overlying first SIPOS layer. A substrate surface at the VLD region is in electrical contact with a second SIPOS layer, and an increased gate-emitter capacitance may be achieved by slightly modifying etch masks during manufacturing. | 01-29-2015 |
Patent application number | Description | Published |
20100018643 | Method And Apparatus For Mounting A Piece Of Foil On A Substrate - An apparatus for mounting a piece of foil on a substrate comprises a holder for receiving a strip of foil which is wound up on a roll, a loop buffer, an alignment unit in which the strip of foil is guided between two parallel plates and is deflected at least twice, a feed unit for the intermittent feeding of the strip of foil and a cutting unit for cutting a piece of foil. The cutting unit comprises two blades which touch each other in a contact point in order to cut the piece of foil. | 01-28-2010 |
20100127599 | ULTRASONIC TRANSDUCER - An ultrasonic transducer comprises an elongate horn, a counterpiece, two piezoelectric drives and a screw. The counterpiece is fastened to the horn by means of the screw and thus clamps the piezoelectric drives, which are arranged on either side of a longitudinal axis of the ultrasonic transducer, between the horn and the counterpiece. The ultrasonic transducer is designed in such a way that the tip of a capillary which is clamped in the horn can oscillate in two different directions. | 05-27-2010 |
20100315655 | Method And Device For Measuring A Height Difference - Determination of the height difference between a first reference point and a second reference point, at least one of the two reference points lying on a semiconductor chip, which is mounted on a substrate, comprises the steps | 12-16-2010 |