Patent application number | Description | Published |
20110214431 | TURBINE GUIDE VANE SUPPORT FOR A GAS TURBINE AND METHOD FOR OPERATING A GAS TURBINE - A turbine guide vane support for an axial-flow gas turbine is provided. The support includes a tubular wall having an inflow-side end and an outflow-side end for a hot gas flowing in the interior of the turbine guide vane support in a flow path of the gas turbine. Cooling channels for a coolant are provided in the wall. The cooling channels extend from a coolant inlet to a coolant outlet, respectively. At least one of the cooling inlets and one of the cooling outlets, respectively, is disposed at the outflow-side end of the turbine guide vane support, wherein the cooling channel associated with the respective inlet and outlet extends up to the inflow-side end of the turbine guide vane support and transitions to a redirecting area from which the respective cooling channel further extends to the outflow-side end. | 09-08-2011 |
20110268580 | Axially segmented guide vane mount for a gas turbine - A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety. | 11-03-2011 |
20120039716 | Guide vane system for a turbomachine having segmented guide vane carriers - A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments. | 02-16-2012 |
20120039719 | Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine - A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root. | 02-16-2012 |
20120107136 | SEALING PLATE AND ROTOR BLADE SYSTEM - A rotor blade system, for example, of a gas turbine is provided. The rotor blade system includes a plurality of rotor blades which are arranged annularly on a rotor disk. A plurality of sealing plates are arranged on a side surface of the rotor disk. An individual sealing plate is formed from a plurality of metal sheets, wherein two of the metal sheets are arranged opposite each other a distance apart and parallel to a plane of the sealing plate, forming a gap for guiding of cooling air. | 05-03-2012 |
20120118524 | CORE DIE WITH VARIABLE PINS AND PROCESS FOR PRODUCING A CORE - A core die is provided. The core die includes a first half and a second half where a cavity is formed between the two. Pins are arranged on the halves and the pins are replaceable. By virtue of the modular inner structure of a core die, the core die may be matched to the desired changes of the core, by small changes, more quickly and more easily than would be the case if the core die had only one part or if the pins were a fixed component of the core die halves. | 05-17-2012 |
20120128504 | Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine - A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face. | 05-24-2012 |
20130207351 | SEAL ARRANGEMENT FOR SEALLING A GAP; AND SEALING ELEMENT FOR THIS PURPOSE - A sealing element for sealing a gap between two components is provided. The sealing arrangement may be a seal arrangement of a gas turbine system, wherein the sealing element is elongate along a main line and has a contoured cross section in a corrugated centre region. In cross section, the sealing element is directed along the main line and may be deformed in a direction substantially orthogonally with respect to the main line. In order to provide a wear-resistant, long-lasting sealing element with a particularly efficient blocking action, it is proposed that the seal teeth of the corrugation have a virtually rectangular cross-sectional contour, the tooth height of which seal teeth is between 10% and 40% of the sealing-element thickness which may be measured parallel to the tooth height. | 08-15-2013 |
20130312249 | METHOD FOR ADJUSTING THE RADIAL GAPS WHICH EXIST BETWEEN BLADE AIRFOIL TIPS OR ROTOR BLADES AND A PASSAGE WALL - A method for measuring and adjusting gaps between a rotor and a stator of a machine using a sensor is provided. The measuring is conducted when the rotor is operated at a rotational speed below a nominal rotational speed of the machine and without the machine being in operation. The adjusting of the gap is carried out as a function of at least one gap dimension of the gap. The sensor is not resistant to an operating temperature of the machine occurring in a region where the sensor is located. After completion of the measuring the machine is operated with the sensor. | 11-28-2013 |