Patent application number | Description | Published |
20080305276 | Method of Applying Hot Gas Anticorrosion Layers - A method for applying hot gas anticorrosion layers to high-temperature-resistant alloys, either nickel-based or cobalt-based alloys, in the form of a gradient layer consisting of one or more elements of the platinum group in combination with aluminum. The components are introduced into a directional high-temperature, high-enthalpy, free jet of solid, liquid or gaseous precursors in mixing ratios such that defined concentration gradients can be established in the layer. | 12-11-2008 |
20090008265 | Method for producing aerodynamic structures during the production of integrally bladed gas turbine rotors - The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor. The contours of the or each of the working electrodes are adapted to the contours of the aerodynamic structure, which are produced by means of the respective working electrode, such that a gap between the rotor disk base body and a working electrode are produced in an approximately identical manner during the removal process of the material; d) electrochemically machining the or each aerodynamic structure in an electrochemical sinking by placing the rotor disk base body and the or each working electrode in an electrolyte and by applying voltage and/or current, whereby the applied current and/or voltage is temporally pulsed; e) pressure-rinsing the gap which is filled with electrolytes between the aero-dynamic structure and the or each working electrode by a pulsed movement of the or each working electrode. | 01-08-2009 |
20090011686 | Peening Chamber for Surface Peening, in Particular for Ultrasonic Shot Peening of Gas Turbine Components - The invention relates to a peening chamber for surface peening, in particular for ultrasonic shot peening of gas turbine components ( | 01-08-2009 |
20090095042 | Method for Surface Blasting Cavities, Particularly Cavities in Gas Turbines - The invention relates to a method for the surface blasting of hollow spaces or cavities, especially of cavities of gas turbines. According to the invention, shot balls are accelerated with the aid of at least one vibrator, whereby the shot balls accelerated in the ultrasonic range are directed onto surfaces of a cavity that is to be blasted. In that regard, the vibrator is preferably positioned with a small spacing distance, preferably with a spacing distance on the order of magnitude of the diameter of the shot balls utilized for the blasting, from the cavity to be blasted. | 04-16-2009 |
20090101521 | Electrode for electrochemical reduction - An electrode ( | 04-23-2009 |
20090107968 | Method For Heating Components - The invention relates to a method for heating a machining area of a structural component, particularly a gas turbine component, prior to and/or during and/or after a machining or processing of the component on the machining area. According to the invention, the machining area ( | 04-30-2009 |
20090110560 | Run-in coating for gas turbines and method for producing same - A run-in coating is for gas turbines. The run-in coating is used for sealing a radial gap between a housing of the gas turbine and rotating rotor blades of same, the run-in coating being applied onto the housing. The run-in coating is made of an intermetallic titanium-aluminum material. | 04-30-2009 |
20090126435 | METHOD FOR THE SURFACE PEENING OF A COMPONENT - The present technology relates generally to a method for surface peening, particularly shot peening, of a component, particularly a gas turbine component, in which peening bodies, particularly peening bodies designed as balls, are directed onto a surface of a component being peened, in order to machine or strengthen the surface of the component. According to certain embodiments of the present technology, the temperature and/or the velocity of the peening bodies is measured to establish process control of surface peening. | 05-21-2009 |
20090258214 | VAPOR-DEPOSITED COATING AND THERMALLY STRESSABLE COMPONENT HAVING SUCH A COATING, AND ALSO A PROCESS AND APPARATUS FOR PRODUCING SUCH A COATING - The present technology relates to a vapor deposited coating for a thermally stressable component, which comprises deliberately introduced pore formers. This distinguishes the coating from the conventional vapor deposited coatings, which, owing to the coating method do not exhibit pores. Moreover, it distinguishes it from sprayed-on coatings, which do not exhibit any pores or only irregularly shaped pores that are formed arbitrarily. In addition, the present technology relates to a method and a device for producing such a coating. | 10-15-2009 |
20090293623 | SONOTRODE ESPECIALLY FOR ACCELERATING SHOT FOR ULTRASONIC SHOT PEENING - A sonotrode for accelerating shot for ultrasonic shot peening, includes at least one vibration exciter and a cover element that has an output side of the sonotrode, wherein the cover element is to be operated by means of the vibration exciter with a forced vibration such that the value of the vibration amplitude of the cover element corresponds essentially to the value of the vibration amplitude of the vibration exciter, where from this cover element another cover element is set out on the further side of the vibration exciter and in which between these two cover elements is stretched a majority of spring elements in the form of tension springs. | 12-03-2009 |
20090301152 | COVER ELEMENT FOR A SONOTRODE AND PEENING CHAMBER ARRANGEMENT FOR THE SURFACE PEENING OF COMPONENTS - A cover element for a sonotrode which is to be configured, in particular, for accelerating peening material within a peening chamber for the surface peening of components and is to be operated by a vibration exciter of the sonotrode, at least one wall, in particular a wall portion of a chamber wall of the peening chamber, being provided, which is mounted in a predefined position on the cover element and is to be moved together with the same is disclosed. In addition, a peening chamber arrangement for the surface peening of components, in particular for ultrasonic shot peening, including a peening chamber that is bounded by at least one chamber wall; and at least one sonotrode having a cover element which includes at least one wall portion of the chamber wall that is to be moved together with the same is disclosed. | 12-10-2009 |
20100006187 | METHOD FOR SURFACE STABILIZING METAL COMPONENTS - The invention relates to a method for the strengthening of the surface of a structural component with the aid of laser shock processing in which a coating applied to a metallic surface of the component to be strengthened is decomposed with the aid of a laser beam provided by a processing laser through evaporation or pyrolysis under creation of a plasma in such a way that a shock wave induced by interaction of the plasma with the metallic surface deforms the surface plastically and with the laser shock processing being monitored by means of recording light emission values of the plasma. In accordance with the invention, the light emission values are recorded with the aid of a measuring laser in time-delayed fashion relative to the decomposition of the coating with the aid of the processing laser. | 01-14-2010 |
20100012507 | METHOD FOR PRODUCING GEAR WHEELS - A method for manufacturing gear wheels, specifically transmission gear wheels, is disclosed. An embodiment of the method includes the following steps: a) preparation of a base body for a gear wheel, b) electrochemical processing of the base body by a precise electrochemical machining process (PECM process), where several recesses running between the teeth of the gear wheel are made simultaneously electrochemically to manufacture the teeth of the gear wheel. | 01-21-2010 |
20100037669 | DEVICE AND METHOD FOR THE SURFACE PEENING OF A COMPONENT OF A GAS TURBINE - A device for surface-peening, especially for the ultrasound shot-peening of a component of a gas turbine, having at least one vibration means that comprises a surface that propels the peening material, and having a holding means with which a surface area of the component and the surface of the vibration means can be arranged with respect to each other is disclosed. In this context, the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component of the gas turbine. Moreover, a method is provided in which the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component. | 02-18-2010 |
20100043512 | DEVICE AND METHOD FOR THE SURFACE PEENING OF A COMPONENT OF A GAS TURBINE - A device for surface peening, in particular for ultrasonic shot peening, of a component of a gas turbine, having at least one vibration device that includes a surface that impinges the blasting material, and having a holding device by which a surface area of the component can be positioned relative to the surface of the vibration device, the surface of the vibration device being subdivided into at least two adjacent partial surfaces, each including an overlapping part by which a part of the surface area of the component can be treated by blasting material impinged both by the one and by the other partial surface. | 02-25-2010 |
20100101698 | METHOD FOR PRODUCING A STRUCTURAL ELEMENT - A method for producing a structural element having a low density and high temperature resistance, where a plurality of hollow spheres made of a high temperature resistant material are connected together in a material fit, is disclosed. Adhesive bridges made of a high temperature resistant, inorganic adhesive are formed between the hollow spheres. The structural mass made of hollow spheres and adhesive is dried and cured at temperatures that are higher than the ambient temperature and are no higher than the subsequent utilization temperature of the structural element. | 04-29-2010 |
20100125990 | METHOD AND DEVICE FOR THE SURFACE PEENING OF A PARTIAL ELEMENT OF A COMPONENT OF A GAS TURBINE - A method and device for the surface peening, especially ultrasonic shot-peening, of at least one partial element of a component of a gas turbine, is disclosed. The partial element, e.g., a sealing fin, and at least one surface of a vibration device impinging the blasting material are positioned relative to each other at an angle between 70° and 90° based on the direction of extension of the sealing fin. | 05-27-2010 |
20100186472 | METHOD AND DEVICE FOR SURFACE PEENING OF A COMPONENT IN THE REGION OF A PASSAGE OPENING - A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region. | 07-29-2010 |
20100193572 | DAMPING DEVICE, WELDING SYSTEM FOR ROTARY FRICTION WELDING AND ROTARY FRICTION WELDING METHOD - The invention relates to a damping device ( | 08-05-2010 |
20100270168 | METHOD FOR REMOVING MATERIAL FROM A COMPONENT, AND ELECTRODE - A method for removing material from a component that is connected as an anode is disclosed. In an embodiment, an electrode that is connected as a cathode is guided to the component such that a gap is formed, an electrolyte is introduced into the gap, and a closed system is formed for the electrolyte by the formation of a duct. The electrolyte is continuously guided from an inlet opening to an outlet opening of the duct. Forming the duct, e.g., by guide elements that are mounted on the electrode, ensures that only those surface parts of the component to be machined from which material is to be removed enter in contact with the electrolyte while the other surface parts do not enter in contact with the electrolyte. Since the electrolyte is continuously guided across the surface, used electrolyte is continuously discharged along with residual matter while fresh electrolyte is delivered. | 10-28-2010 |
20100272572 | METHOD FOR PRODUCING AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for producing an integrally bladed rotor, as well as a rotor, is disclosed. A rotor support is composed of several disk-type rotor base bodies that are welded onto the blade ring. | 10-28-2010 |
20100294647 | METHOD AND DEVICE FOR PLASMA REFORMATION OF FUEL FOR ENGINE APPLICATIONS - The invention relates to a method for plasma reformation of fuel, in particular kerosene, which method comprises the steps of: | 11-25-2010 |
20100319194 | METHOD FOR PRODUCING INTEGRALLY BLADED ROTORS - A method for producing integrally bladed rotors comprises the following steps: a) defining and providing a blade profile of a blade to be manufactured with a pre-contour and a theoretical contour; b) producing at least two sectional planes of the blade profile, which sectional planes run vertically to a threading axis of the blade profile and of the blade to be manufactured; c) determining a point of rotation per sectional plane to produce an interval between the pre-contour and the theoretical contour that is approximately the same circumferentially, which points of rotation are located on a connecting line running parallel to the threading axis; and d) providing a base rotor body and electrochemically working the base rotor body in order to produce a raw blade with the blade pre-contour by movement of a hollow electrode into the base rotor body, the electrode movement including advancing motion along the connecting line superposed by rotation at the points of rotation, and which hollow electrode has an inner contour adapted to the pre-contour of the raw blade at least in an end area that is moved into the base rotor body. | 12-23-2010 |
20110002789 | METHOD FOR PRODUCING AND REPAIRING A PART, AND PART OF A GAS TURBINE - The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method. | 01-06-2011 |
20110129353 | METHODS FOR JOINING A MONOCRYSTALLINE PART TO A POLYCRYSTALLINE PART BY MEANS OF AN ADAPTER PIECE MADE OF POLYCRYSTALLINE MATERIAL - The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of:—joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and—joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material. | 06-02-2011 |
20110186442 | METHOD FOR MACHINING A METAL COMPONENT - The invention concerns a method for the machining of a metallic structural component, particularly a structural component of a gas turbine, by means of finishing with a pulsed electrochemical ablation process, whereby the structural component features a pre-contour, to be finished, with different over-measures. The method is characterized by the following processing steps: a) determination of the different over-measures of the pre-contour, and b) bilateral and simultaneous finishing by means of a simultaneous feed of respectively at least one electrode disposed on different sides of the structural component, whereby the feed velocity of the electrode in the area of the largest over-measure of the pre-contour is higher than the feed velocity in the area of the smaller over-measure of the pre-contour. | 08-04-2011 |
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 |
20110219616 | METHOD FOR REPLACING AN INNER DISK ELEMENT OF AN INTEGRALLY BLADED DISK - The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored. | 09-15-2011 |
20110287249 | ANTI-EROSION LAYER FOR AERODYNAMIC COMPONENTS AND STRUCTURES AND METHOD FOR THE PRODUCTION THEREOF - An anti-erosion layer is provided for aerodynamic components or structures and to a method for producing such a layer. Microscale or nanoscale hard material particles are embedded in a binding layer that includes a material that adheres to the aerodynamic component or structure. The anti-erosion layer can be applied by spraying or by evaporation coating. | 11-24-2011 |
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 |
20120213659 | METHOD AND DEVICE FOR PRODUCING A COMPONENT OF A TURBOMACHINE - A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed. | 08-23-2012 |
20120217226 | METHOD AND DEVICE FOR PRODUCING A COMPONENT OF A TURBOMACHINE - The invention relates to a method for producing a component ( | 08-30-2012 |
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 |
20130056365 | METHOD AND ELECTRODE FOR ELECTROCHEMICALLY PROCESSING A WORKPIECE - A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area. | 03-07-2013 |
20130084421 | METHOD FOR PRODUCING A COMPONENT AND SUCH A COMPONENT - The invention relates to a component, which has a layer applied by gas dynamic cold spray, said layer having at, least one layer section or a reinforcing element, the material and orientation of which are selected according to a load line, and to a method for producing such a component by gas dynamic cold spray. | 04-04-2013 |
20130118180 | Exhaust Gas Treatment Of Gas Turbine Engines - A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device. | 05-16-2013 |
20130129976 | COATING PLASTIC COMPONENTS BY MEANS OF KINETIC COLD GAS SPRAYING - A method for coating a plastic surface and a plastic component is disclosed. The method includes applying a base layer to a plastic surface. A layer of a coating is applied by kinetic cold gas spraying on the base layer. The base layer is applied by a method that is different from the kinetic cold gas spraying. The base layer adheres to the plastic surface and the layer of the coating applied by kinetic cold gas spraying is deposited on the base layer by the kinetic cold gas spraying. | 05-23-2013 |
20130189086 | SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed. | 07-25-2013 |
20130236300 | HOUSING AND TURBOMACHINE - A housing for a turbomachine includes a peripheral wall delimiting an annular space and a fluid conveying system for redirecting a partial flow of a main flow, which has an axial channel, a front annular channel and a rear annular channel in fluid connection with the axial channel and having a front annular space opening and a rear annular space opening. The fluid conveying system has a front valve device and a rear valve device controllable independently of the front valve device, for opening and closing the annular space openings, and an outlet opening for tapping the partial flow from the fluid conveying system. In the closed state of the rear annular space opening, the partial flow is directable through the rear annular channel and, in the closed state of the front annular space opening, the partial flow is directable through the front annular channel. | 09-12-2013 |
20130280439 | METHOD FOR THE LAYERED MANUFACTURING OF A STRUCTURAL COMPONENT AND DEVICE - The invention relates to a method for the layered manufacturing of a structural component from powder, comprising the following steps: establishing at least one parameter (t) of a depression ( | 10-24-2013 |
20130287590 | GENERATIVELY PRODUCED TURBINE BLADE AND DEVICE AND METHOD FOR PRODUCING SAME - The present invention relates to a method for producing gas turbine components, in particular aircraft turbine components, preferably low-pressure turbine blades, from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, wherein the sintering is carried out in a closed first housing ( | 10-31-2013 |
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 |
20140044938 | Process for producing a COMPONENT-MATCHED PROTECTIVE LAYER and component having such a protective layer - Disclosed is process for producing a protective layer for protecting a component against high temperatures and aggressive media. The process comprises forming a surface layer comprising aluminum and chromium on a surface of the component to be provided with the protective layer by chromizing and alitizing. The chromizing and/or the alitizing in different regions of the component surface to be protected is carried out simultaneously but differently to result in a protective layer that has different regions. | 02-13-2014 |
20140044986 | DUPLEX-PHASE CrAl COATING FOR IMPROVED CORROSION/OXIDATION PROTECTION - Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing. | 02-13-2014 |
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 |
20140072823 | GENERATIVE PRODUCTION METHOD AND POWDER THEREFOR - The invention relates to a generative production method for producing a component by selectively melting and/or sintering a powder several times consecutively by introducing an amount of heat by means of beam energy, such that the powder particles melt and/or sinter in layers, wherein the powder particles ( | 03-13-2014 |
20140161624 | METHOD FOR PRODUCING A RUN-IN COATING, A RUN-IN SYSTEM, A TURBOMACHINE, AS WELL AS A GUIDE VANE - A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating. | 06-12-2014 |
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 |
20140294570 | TURBOMACHINE - Disclosed are a turbomachine having at least one radial gap seal which has at least two opposite ceramic coatings which are constructed in each case from a ceramic powder, the particle size of which is smaller than 1.0 μm, and a turbomachine having at least one radial gap seal, wherein the coatings are built up from powder-based individual layers, the outer layer of which has a higher ceramic fraction than a base layer close to the rotor or stator section respectively, wherein the particle size of the powder material is smaller than 1.0 μm. | 10-02-2014 |
20150016974 | METHOD OF PRODUCING AN INSULATION ELEMENT AND INSULATION ELEMENT FOR A HOUSING OF AN AERO ENGINE - The invention relates to a process for producing an insulation element ( | 01-15-2015 |