Abstract: The present disclosure provides compositions, articles, and methods related to altering electromagnetic radiation. An actinic radiation curable precursor composition of a three-dimensional article includes a) a resin comprising an actinic radiation curable component, wherein the resin has a viscosity no greater than 500 cP; b) hollow glass microspheres having a density no greater than 2 g/mL and an average diameter no greater than 200 micrometers; and c) a photoinitiator. At least part of the surface of the hollow glass microspheres comprises a surface coating or modification. An article includes a photo(co)polymerization reaction product of the composition. A method of manufacturing a three-dimensional article includes the steps of a) providing an actinic radiation curable precursor composition; and b) selectively exposing a portion of the composition to a source of actinic radiation to at least partially cure the exposed portion of the composition, thereby forming a cured layer.

Abstract: The present disclosure provides methods, articles, and apparatuses related to altering electromagnetic radiation. A method of making articles includes a) forming an electromagnetic radiation altering material by providing a polymer matrix and optionally embedding dielectric particles in the polymer matrix and b) obtaining initial dielectric properties of the electromagnetic radiation altering material. The method further includes c) modeling electromagnetic radiation altering features of the material suitable for the article obtained from the material to have target electromagnetic radiation altering properties, thereby obtaining a simulation of the electromagnetic radiation altering article; and d) additive manufacturing the electromagnetic radiation altering article based on the simulation of the electromagnetic radiation altering article. An electromagnetic radiation altering article obtained by the method is also provided.

Abstract: A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.

Abstract: A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

Abstract: The present invention relates to a method for testing a component, in particular an aircraft engine, comprising the steps of: determining (S40) a value of a first toleranced parameter (A1; A2) of the component; determining (S50) a value of a second toleranced parameter (E1; ...; E4) of the component; and classifying (S70) the component in a predefined quality class if this value pair lies outside of a predefined tolerance range, the upper and/or lower limit (G) of which for the second parameter depends on the first parameter, in particular linearly, in at least one first permissible value range (Ta1,1) of the first parameter.

Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.

Abstract: A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.

Abstract: A method for examining a component with the steps: Determining an actual value of a first parameter of a first characteristic of the component; Determining an actual value of the first parameter of at least one further characteristic of the component; Determining a first statistical characteristic variable of these actual values of the first parameter; and Classifying the component on the basis of the first statistical characteristic variable and the actual values of the first parameter, wherein the component is classified in a predetermined quality class if the first statistical characteristic variable is outside a predetermined first characteristic variable range or at least one of these actual values of the first parameter is outside a predetermined first range of values.

Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.

Abstract: The invention refers to a method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

Abstract: A turbomachine having a flow channel (6) and a housing (1, 2) which radially surrounds the flow channel, at least one sealing or lining element (11) being situated between the flow channel and the housing, at least one clamping ring (14) being provided, which is situated circumferentially around the flow channel and which is situated in such a way that it abuts at least one contact surface (22) of the at least one sealing or lining element (11).

Abstract: A fast response temperature probe which may be used for a method for measuring an instantaneous temperature of a periodically changing fluid flow within a gas turbine is proposed. The temperature probe includes a substrate and a resistive element arranged at a surface of the substrate. Therein, at least at a surface of the substrate contacting the resistive element, the substrate comprises an insulating material having a thermal product of less than 1.5 kJ/(m2K sqrt(s)). The substrate or at least its surface is made from polyamide-imide such as for example fiber-reinforced Torlon© 5030. The temperature probe may allow measurements of instantaneous local temperatures of very fast fluctuations of more than 50 kHz at high spatial resolutions of, e.g., less than 0.5 mm2. The instantaneous temperature of a periodically changing fluid flow may be determined by correlating first and second sets of temperature measurements taking into account the periodicity of the periodically changing fluid flow.

Abstract: A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall (2) that delimits the flow channel and an outer wall (1) that is closed off vis-à-vis the environment. A heat-protection plate (3) is arranged on the radial outside of the inner wall, and insulation (4) is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel (6) is formed between the insulation and the radial inside of the outer wall, the cooling-air channel (6) having at least one air-guiding element (5) resting against the insulation.

Abstract: A gas turbine jet engine having a main flow channel and a housing structure which radially surrounds this main flow channel. A housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly. The flow of the housing gas flow to and/or along the main flow channel may be adjusted by adjusting a flow conducting sheet.

Abstract: A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall (2) that delimits the flow channel and an outer wall (1) that is closed off vis-à-vis the environment. A heat-protection plate (3) is arranged on the radial outside of the inner wall, and insulation (4) is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel (6) is formed between the insulation and the radial inside of the outer wall, the cooling-air channel (6) having at least one air-guiding element (5) resting against the insulation.

Abstract: A gas turbine jet engine having a main flow channel (20) and a housing structure (22) which radially surrounds this main flow channel, in which a housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly (25), with the aid of which the flow of the housing gas flow to and/or along the main flow channel may be adjusted.

Abstract: A turbomachine having a flow channel (6) and a housing (1, 2) which radially surrounds the flow channel, at least one sealing or lining element (11) being situated between the flow channel and the housing, at least one clamping ring (14) being provided, which is situated circumferentially around the flow channel and which is situated in such a way that it abuts at least one contact surface (22) of the at least one sealing or lining element (11).

Abstract: A fast response temperature probe which may be used for a method for measuring an instantaneous temperature of a periodically changing fluid flow within a gas turbine is proposed. The temperature probe includes a substrate and a resistive element arranged at a surface of the substrate. Therein, at least at a surface of the substrate contacting the resistive element, the substrate comprises an insulating material having a thermal product of less than 1.5 kJ/(m2K sqrt(s)). The substrate or at least its surface is made from polyamide-imide such as for example fibre-reinforced Torlon© 5030. The temperature probe may allow measurements of instantaneous local temperatures of very fast fluctuations of more than 50 kHz at high spatial resolutions of, e.g., less than 0.5 mm2. The instantaneous temperature of a periodically changing fluid flow may be determined by correlating first and second sets of temperature measurements taking into account the periodicity of the periodically changing fluid flow.