Patent application number | Description | Published |
20090304497 | GUIDE BLADE SEGMENT OF A GAS TURBINE AND METHOD FOR ITS PRODUCTION - A guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, is disclosed. An integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor. | 12-10-2009 |
20090324384 | GAS TURBINE HAVING A PERIPHERAL RING SEGMENT INCLUDING A RECIRCULATION CHANNEL - A gas turbine having at least one compressor, at least one combustion chamber, and at least one turbine, the or each compressor and/or the or each turbine having a rotor that includes rotor blades surrounded by a stationary housing, and a run-in coating being assigned to the housing is disclosed. The gas turbine includes at least one channel which is configured to apply a pressure prevailing on the high-pressure side of the blades of a rotor to a low-pressure side of the same in the area of a gap between the radially outer ends of the blades and the housing and thereby prevent a flow through the gap. | 12-31-2009 |
20110052412 | HIGH-PRESSURE TURBINE ROTOR, AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a high-pressure turbine rotor, as well as a turbine rotor, is disclosed. The turbine rotor is designed as a blisk (i.e., bladed disk) and forms a radially inward disk and several vanes or blades that project from the disk. The turbine rotor has an internal duct system for air cooling and at least one section of the turbine rotor is manufactured in a generative production process. | 03-03-2011 |
20110217457 | REPAIR METHOD - A method for repairing gas turbine components, in particular gas turbine blades, including at least the following steps: a) preparing a gas turbine component to be repaired; b) removing a damaged portion from the gas turbine component to be repaired, thereby forming a plane separation surface; c) placing the gas turbine component at least partly in a process chamber in such a way that the plane separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a metal powder that is bonding-compatible with the material of the gas turbine component to be repaired, namely up to the level of the separation surface; e) building up the removed portion on the separation surface by depositing metal powder in layers onto the separation surface and by fusing the metal powder, which has been deposited in layers onto the separation surface, to the separation surface. | 09-08-2011 |
20120171041 | THIN-WALLED STRUCTURAL COMPONENT, AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support ( | 07-05-2012 |
20120219726 | METHOD AND DEVICE FOR PRODUCING A COMPONENT - The invention relates to a method for producing a component ( | 08-30-2012 |
20130055568 | METHOD AND DEVICE FOR PRODUCING A COMPONENT - A method for manufacturing a component, in particular a component of a turbine or a compressor, in which at least these steps are carried out: application in layers of at least one powdered component material to a component platform in the area of a buildup and joining zone; melting and/or sintering locally in layers of the component material by supplying energy with the aid of at least one electron beam in the area of the buildup and joining zone; lowering of the component platform in layers by a predefined layer thickness; and repeating steps a) through c) until completion of the component. During the manufacturing, electrons emitted due to the interaction of the electron beam with the component material are detected, after which material information, characterizing the topography of the melted and/or sintered component material, is ascertained on the basis of the emitted electrons. Alternatively or additionally, the component material is melted and/or sintered by at least two, preferably at least four electron beams. | 03-07-2013 |
20130294891 | METHOD FOR THE GENERATIVE PRODUCTION OF A COMPONENT WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE, AND A COMPONENT PRODUCED IN A GENERATIVE MANNER WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE - The invention provides a method for the generative manufacture of a component ( | 11-07-2013 |
20130343947 | METHOD AND DEVICE FOR PROCESS MONITORING - Disclosed is a method for monitoring a generative production process in real time, wherein a component is at least optically detected and the installation space is thermally detected when applying a layer, as well as a device for carrying out said method. | 12-26-2013 |
20140065343 | DEVICE FOR PRODUCING, REPAIRING AND/OR REPLACING A COMPONENT BY MEANS OF A POWDER THAT CAN BE SOLIDIFIED BY ENERGY RADIATION, METHOD AND COMPONENT PRODUCED ACCORDING TO SAID METHOD - The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit. | 03-06-2014 |
20140239553 | MULTI-FREQUENCY INDUCTION HEATING OF GENERATIVELY PRODUCED COMPONENTS - The invention relates to a method and device for generatively producing components, said device comprising a radiation device for selectively radiating a powder bed, and an induction device for inductively heating the component produced by radiating the powder bed, Said induction device comprising at least one voltage source which can simultaneously produce alternating voltages with at least two different frequencies. | 08-28-2014 |
20140334924 | METHOD AND DEVICE FOR THE GENERATIVE PRODUCTION OF A COMPONENT USING A LASER BEAM AND CORRESPONDING TURBO-ENGINE COMPONENT - In a method for the generative production of a component ( | 11-13-2014 |
20150030434 | DAMPING DEVICE FOR BEING SITUATED BETWEEN A HOUSING WALL AND A CASING RING OF A HOUSING OF A THERMAL GAS TURBINE - A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided. | 01-29-2015 |