Patent application number | Description | Published |
20080202650 | Heat Treatment Method For Monocrystalline or Directionally Solidified Structural Components - The invention relates to a heat treatment method for monocrystalline or directionally solidified structural components. Said method comprises a heat treatment which results in dissolving at least one crystalline phase of the material of the structural component, referred to in the following as component material. The inventive method is characterized by carrying out the heat treatment by heating the structural component to a dissolution temperature required for dissolving the crystalline phase only in at least one first component area in which the stresses within the component material do not exceed a predetermined value. In at least one second component area in which the stresses within the component material exceed the predetermined value the material is only heated to a temperature below the dissolution temperature. | 08-28-2008 |
20080202718 | Process For Producing A Lost Model, And Core Introduced Therein - The invention relates to a method for the production of a pattern for precision casting representation of turbine component comprising at least one cavity, whereby the prepared pattern comprises at least one core and an outer contour pattern, at least partly enclosing the core and at least partly defining the outer contour of the turbine component. The core is made from a hardening core material, which hardens during the course of the method and the outer contour pattern is made from a combustible or fusible material. The outer contour model is first produced with at least one cavity corresponding to the at least one cavity of the turbine component and subsequently, in order to form the at least one care, the hardening core material is introduced into the at least one cavity and hardened. | 08-28-2008 |
20090107592 | Heat treatment of alloys having elements for improving grain boundary strength - Heat treatment of alloys having elements for improving grain boundary strength | 04-30-2009 |
20090285715 | Welding Additive Material, Welding Methods And Component - The invention relates to a welding additive material, a use of a welding additive material, welding methods and a component which significantly improves the weldability of some nickel-based superalloys by means of a welding additive material and comprises the following constituents (in wt %): 18.0%-20.0% of chromium, 9.0%-11.0% of cobalt, 7.0%-10.0% of molybdenum, 2.0%-2.5% of titanium, 1.0%-1.7% of aluminum, 0.04%-0.08% of carbon, balance nickel. | 11-19-2009 |
20100000976 | Process for Repairing a Component Comprising a Directional Microstructure by Setting a Temperature Gradient During the Laser Heat Action, and a Component Produced by Such a Process - In one aspect, a repair method for repairing components comprising a base material with a directed microstructure is provided. The repair is performed in such a way that the repaired location correspondingly has a directed microstructure like the surrounding base material. A solder is applied in the region of a location to be repaired and is soldered to the component via heat exposure, a temperature gradient, i.e., for instance a temperature variation from a higher temperature to a lower temperature, is thereby produced in the region of the location to be repaired. | 01-07-2010 |
20100294451 | Method for producing a pattern for the precision-cast preparation of a component comprising at least one cavity - A method for producing a pattern for the precision-cast representation of a component having a cavity is provided. In the method wherein the component is a turbine component having a cavity, the finished pattern comprises a core and an outer contour pattern, the outer contour pattern at least partially surrounds the core and at least partially defines the outer contour of the turbine component. The core is produced from a curable core material, which cures during the course of the method, and the outer contour pattern is produced from a material which can be burned or melted out. In this case, first the outer contour pattern is produced with a cavity corresponding to the cavity of the turbine component and subsequently the curable core material is filled into the cavity and cured to produce the core. | 11-25-2010 |
20120039718 | CASTING APPARATUS FOR PRODUCING A TURBINE ROTOR BLADE OF A GAS TURBINE AND TURBINE ROTOR BLADE - A casting apparatus for producing a turbine rotor blade of a gas turbine, and to a turbine rotor blade produced therewith is provided. The casting apparatus includes a hollow ceramic shell mold, of which the pouring gate and cores arranged therein are oriented with respect to each other such that a hot casting material flowing into a cavity of the ceramic shell mold does not come in direct contact with the cores. Thus, so-called hot spots on cores are avoided, which until now have had negative effects on the solidification of the casting material. Especially in the region of the blade root of the turbine rotor blade to be produced improved solidification of the casting material may thus be obtained, reducing any disturbance in the structure of the solidified casting material. | 02-16-2012 |
20120103554 | PROCESS FOR OPTIMIZING A CORE DIE - A process for optimizing a core die is provided. By iteratively modifying the ceramic core without changing the core die, it is possible to ascertain an optimum core without modifying the core die every time. In a last step, an optimum core die is produced using the optimum ceramic core. | 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 |
20120175027 | Heat Treatment of Alloys Having Elements for Improving Grain Boundary Strength - A method of producing a component wherein a directionally solidified columnar grained cast superalloy material is heat treated such that a secondary phase of the alloy is only partly solved, thereby providing improved transverse stress rupture strength compared to fully solved alloys. | 07-12-2012 |
20120273153 | Casting mold having a stabilized inner casting core, casting method and casting part - A casting mold for a metal melt is provided. By coating a core of a casting mold, the core may be mechanically stabilized and an inner coating of the component to be cast may be obtained, wherein the coating preferably serves as an anti-corrosion layer. A method for producing a cast part using the casting mold is also provided. | 11-01-2012 |
20120285652 | Liner for a Die Body - A liner for a die body is presented. The liner includes a flexible base material characterized in that reinforcements with lower stretchability compared to the base material are bonded along the extent of the liner. A tool which includes the liner is also provided. The reinforcements may include glass fibers or carbon fibers. | 11-15-2012 |
20130136649 | DS SUPERALLOY AND COMPONENT - A nickel-based DS alloy for directional solidification, includes Cobalt (Co), Chromium (Cr), Molybdenum (Mo), Tungsten (W), Tantalum (Ta), Titanium (Ti), Aluminum (Al), Rhenium (Re), Hafnium (Hf), Boron (B), Carbon (C), and Zirconium (Zr). Further, a component, for example a turbine blade or vane, with such an alloy is provided. | 05-30-2013 |
20130330203 | METHOD FOR PRODUCING A PROTECTIVE LAYER FOR A ROTOR BLADE - A method for producing a protective layer for a rotor blade of a turbomachine is proposed. The rotor blade has a wear cap wall that in relation to the axis of the turbomachine protrudes radially towards the exterior of the turbomachine beyond a body of the rotor blade. The method enables the entire rotor blade to have a comparatively long service life and at the same time allows the wear cap wall to be thermally insulated in an especially simple manner. For the purpose, a profile producing a positive fit effective in the radial direction is inserted in a radially located region of the wear cap wall, a slip containing metal powder and/or a ceramic slip is applied to the region and the slip in sintered. | 12-12-2013 |
20140099209 | GAS TURBINE COMPONENT, METHOD FOR ITS PRODUCTION AND CASTING MOLD FOR USE OF THIS METHOD - A method is provided for casting a gas turbine component having at least a first section and a second section. As per the method, a liquid metal is cast into a casting mold and solidification of the metal is induced by means of controlled cooling. The cooling of the liquid metal in the first section is controlled in such a way that the metal solidifies in a directionally solidified crystal structure or a single-crystal structure. In the second section the cooling is carried out in such a way that it solidifies in a multidirectional crystal structure. | 04-10-2014 |
20140255652 | SURFACE HAVING SPECIALLY FORMED RECESSES AND COMPONENT - A surface having specially formed recesses and component is provided. The component has a layer with a surface, having elongate recesses, which have a longitudinal direction, wherein the recesses are arranged at an angle which differs considerably from 0°, in particular 90°+/−20°, with respect to a direction of overflow over the surface, and are at least partially widened transversely to the longitudinal direction thereof in the region of the surface with respect to the base of the recess, in which the recess is widened proceeding from the base only above a certain height within the recess, and in particular the recess has a constant width before it, in which the recess does not extend through the entire thickness of the layer. | 09-11-2014 |
20150017014 | CORE FOR CASTING A HOLLOW COMPONENT | 01-15-2015 |