Abstract: Various embodiments of the teachings herein include an electric motor. In some embodiments, the motor includes: a stator; and a moving component comprising an iron-based soft-magnetic structural material including crystallites of a ferromagnetic iron-based alloy separated by grain boundaries, wherein there is interlayer-free contact between the crystallites at grain boundaries. The structural material comprises ceramic fibers. A content of the ceramic fibers is between 0.2% and 10% by volume. An aspect ratio of the ceramic fibers is less than 0.1.

Abstract: There is provided a component formed from a plurality of laminates stacked on one another, thereby defining a stacked laminate structure having a leading edge and a trailing edge. Each of the plurality of laminates is formed from a ceramic matrix composite material. In addition, a plurality of interior cooling channels are defined within an interior of the stacked laminate structure and extend longitudinally between the leading edge and the trailing edge. A metal support structure is arranged so as to extend through first openings in the laminates and through the stacked laminate structure.

Abstract: A hybrid component (45) is provided including a plurality of laminates (10) stacked on one another to define a stacked laminate structure (58). The laminates (10) include a ceramic matrix composite material (22) and at least one opening (24) defined therein. A metal support structure (56) may be additively manufactured through each opening (24) so as to extend through the stacked laminate structure (58).

Abstract: The embodiments relate to a method for the production of a refractory metal component by casting. The method includes providing a slip that contains a powder including at least one refractory metal or a compound thereof, in addition to at least one binding agent. The method further includes processing the slip by casting, (e.g., film casting or slip casting), to form at least one slip coating, the slip being devoid of a metal binding agent. A component was produced by this method. The embodiments may be used, in particular, on X-ray tubes, accelerator targets, or fusion reactors, such as for a surface of an X-ray anode, or a wall of a fusion reactor.

Abstract: A hybrid component is provided including a plurality of laminates stacked on one another to define a stacked laminate structure. The laminates include a ceramic matrix composite material having certain features, such as a matrix porosity characteristic and a hierarchical fiber architecture, and at least one opening defined therein. A metal support structure may be arranged through each opening so as to extend through the stacked laminate structure.

Abstract: A gas turbine arrangement, a power plant having such a gas turbine arrangement and a method for operating the power plant are provided. A compressor may be mechanically coupled to a turbine which can be driven by combustion gases, such as can be generated by combustion of fuel with the compressed combustion air. An exhaust system may be used to discharge the combustion gases. One or more thermoelectric generators may be thermally coupled to the exhaust system for generating electrical energy from residual heat of the combustion gases which pass in the exhaust system. This gas turbine arrangement allows waste heat from the combustion gases to be utilized and thus the overall efficiency of the gas turbine arrangement can be increased and pollutant emissions may be lowered.

Abstract: A rotary anode for an X-ray tube includes a ceramic base body that carries a focal path for emitting X-rays during electron irradiation. The ceramic base body is made of a mixture of silicon carbide and at least one high temperature-resistant diboride.

Abstract: A layer system is provided having a substrate, an outermost layer with a surface, at least one hole at least in the outermost layer, wherein in the vicinity around the hole or directly adjoining a boundary line of the hole, at least one, not closed extending recess is present in the surface of the outermost layer in which the recess is curved and its ends face each other. Through the use of depressions in a layer, spalling within the interfaces through the layers is prevented.

Abstract: A method of manufacturing a superalloy compound component is provided. The component includes a first component portion primarily consisting of a first superalloy and a second component portion primarily consisting of a second superalloy or of a refractory metal. The method includes using Spark Plasma Sintering for forming the superalloy compound component.

Abstract: A thermal barrier tile (34) with a braze layer (46) co-sintered to a ceramic layer (48), optionally with a layer of MCrAlY bond material (74) disposed there between. The tile can be brazed to a substrate (26) of a component for fabrication or repair of a thermal barrier coating (28). The tile may be fabricated by disposing a first layer of a metal brazing material in a die case (40); disposing a second layer of a ceramic powder on the metal brazing material; and co-sintering the two layers with spark plasma sintering to form the co-sintered ceramic/metal tile. The tile may include an interlocking structural pattern (56) at the ceramic/braze interface, and further may include mirror image contoured edges (70) for interlocking of tiles that are disposed side-by-side. Heights of adjacent tiles (34F, 34G) may be different to improve abradability of the surface.

Abstract: Thermoelectric elements of a thermoelectric transducer are p-doped and n-doped and are arranged alternately, connected electrically to one another and are formed essentially in the shape of a ring.

Abstract: A gas turbine is provided having a heat flow sensor which is arranged on a surface of a component of the gas turbine and which is designed as a thermal element, wherein the heat flow sensor is a transverse thermoelectric element.

Abstract: The embodiments relate to a method for the production of a refractory metal component by casting. The method includes providing a slip that contains a powder including at least one refractory metal or a compound thereof, in addition to at least one binding agent. The method further includes processing the slip by casting, (e.g., film casting or slip casting), to form at least one slip coating, the slip being devoid of a metal binding agent. A component was produced by this method. The embodiments may be used, in particular, on X-ray tubes, accelerator targets, or fusion reactors, such as for a surface of an X-ray anode, or a wall of a fusion reactor.

Abstract: A thermal barrier tile (34) with a braze layer (46) co-sintered to a ceramic layer (48) is brazed to a substrate (26) of a component for fabrication or repair of a thermal barrier coating (28) for example on a gas turbine ring segment (22, 24). The tile may be fabricated by disposing a first layer of a metal brazing material in a die case (40); disposing a second layer of a ceramic powder on the metal brazing material; and co-sintering the two layers with spark plasma sintering to form the co-sintered ceramic/metal tile. A material property of an existing thermal barrier coating to be repaired may be determined (90), and the co-sintering may be controlled (93) responsive to the property to produce tiles compatible with the existing thermal barrier coating in a material property such as thermal conductivity.

Abstract: A manufacturing method for manufacturing a slice for making or repairing a heat protective coating of a hot gas path component of a gas turbine is provided. The manufacturing method includes debinding a prepreg made of at least two sheets containing powder bound by a binder and Spark Plasma Sintering the at least two debound sheets.

Abstract: A rotating anode includes a focal track that has a microstructure on a surface of the focal track. The microstructure is produced using deep reactive ion etching.

Abstract: A thermal barrier tile (34) with a braze layer (46) co-sintered to a ceramic layer (48) is brazed to a substrate (26) of a component for fabrication or repair of a thermal barrier coating (28) for example on a gas turbine ring segment (22, 24). The tile may be fabricated by disposing a first layer of a metal brazing material in a die case (40); disposing a second layer of a ceramic powder on the metal brazing material; and co-sintering the two layers with spark plasma sintering to form the co-sintered ceramic/metal tile. A material property of an existing thermal barrier coating to be repaired may be determined (90), and the co-sintering may be controlled (93) responsive to the property to produce tiles compatible with the existing thermal barrier coating in a material property such as thermal conductivity.

Abstract: A gas turbine arrangement, a power plant having such a gas turbine arrangement and a method for operating the power plant are provided. A compressor may be mechanically coupled to a turbine which can be driven by combustion gases, such as can be generated by combustion of fuel with the compressed combustion air. An exhaust system may be used to discharge the combustion gases. One or more thermoelectric generators may be thermally coupled to the exhaust system for generating electrical energy from residual heat of the combustion gases which pass in the exhaust system, This gas turbine arrangement allows waste heat from the combustion gases to be utilized and thus the overall efficiency of the gas turbine arrangement can be increased and pollutant emissions may be lowered.

Abstract: A method for repairing a damaged portion (144) of a brazed-on gas turbine engine seal (142) without the need to remove and to replace the entire seal. The damaged portion is removed to reveal a repair surface (146) of the underlying superalloy material, and a new seal structure (148) is formed by an additive manufacturing processes using a laser beam (124) to melt a powder (116) including superalloy material (116?) and flux material (116?). The flux material forms a protective layer of slag (132) over the melted superalloy material, thereby permitting the new seal structure to be formed directly onto the underlying superalloy material without the need for an intervening braze layer.

Abstract: Thermoelectric elements of a thermoelectric transducer are p-doped and n-doped and are arranged alternately, connected electrically to one another and are formed essentially in the shape of a ring.