Abstract: A heat exchanger, in particular a tubular heat exchanger, a tube bundle heat exchanger, a finned tube heat exchanger and a plate heat exchanger, having at least one elongate flow duct through which a fluid is conducted during operation in a main flow direction corresponding to the longitudinal extent of the flow duct. The at least one flow duct has internal components and/or design features which give the fluid flowing in the main flow direction a swirl in a circumferential direction of the flow duct. A heat pump includes at least one such heat exchanger.

Abstract: Ceramics or ceramic layer systems can be machined due to the use of high speeds of an EDM electrode. Disclosed is a method and an EDM device for carrying out the method for drilling ceramics or ceramic-coated components, which uses an EDM electrode and wherein the EDM electrode is rotated at a speed of at least 1000 rpm, in particular of at least 10,000 rpm, for drilling through the ceramic or through the ceramic-coated component.

Abstract: Cooling holes in a turbine component, such as a blade, vane or combustor transition, are formed in and surrounded by a micro surface feature (MSF) that protects the adjoining thermal barrier coating (TBC) from delamination or crack propagation during the hole formation or during engine operation. The MSF effectively functions as a circumferential sleeve around the cooling hole margin so that relatively more friable TBC material that would otherwise define the cooling hole margin is not directly exposed to coolant fluid exhausting the hole, foreign object damage (FOD) or contact with cooling hole formation tooling when fabricating the hole through the TBC layer. The MSF is formed as a projection from the component substrate or during subsequent application of a metallic bond coat (BC) layer.

Abstract: Known protective coatings with a high Cr-content and silicon as an additive have brittle phases which become additionally brittle under the influence of carbon during use. The protective coating herein has a double metallic layer that only contains tantalum on the outside contents of the layers.

Abstract: Known protective layers having high Cr content and additional silicon form brittle phases, which additionally become brittle under the effect of carbon during use. The protective layer according to the invention comprises a two-part metal layer, which contains tantalum on the outside.

Abstract: A method is provided for treating turbine blades having holes for discharging cooling air. A protective layer is provided and then the holes that are partly or completely closed by the protective layer are opened again. Coordinates concerning the position of the holes are acquired before the protective layer is applied using a laser triangulation sensor using a light source generating a light beam and a light detector. The data obtained is used after application of the protective layer to control a removal device for removing protective layer partly or wholly covering the holes. Each hole is measured by the light beam being shone into the hole in different positions in relation to the longitudinal mid-axis of the latter. The light beam is shone into the respective hole in a plane at at least three different angles to the longitudinal mid-axis thereof.

Abstract: A method and system for automated repair of a machine component is provided. According to the proposed method, a first geometry of the component, including a damaged portion of the component, is digitalized. A trough is then machined over the damaged portion of the component. The machining is numerically controlled using digitalized geometrical data of the first geometry of the component. A second geometry of the component is then digitalized subsequent to the machining, the second geometry including the trough. Subsequently, a material is deposited over the trough. The deposition of the material is numerically controlled digitalized geometrical data of the second geometry of the component.

Abstract: During the coating of a component including cooling-air holes, it is necessary, when remachining the coated cooling-air holes, to determine the correct alignment of the cooling-air row. A process is provided in that at least two cooling-air holes are kept clear by a masking material during the coating and the alignment of the cooling-air row is effected on the basis of these two unclosed cooling-air hole.

Abstract: Known protective coatings with a high Cr-content and silicon as an additive have brittle phases which become additionally brittle under the influence of carbon during use. The protective coating herein has a double metallic layer that only contains tantalum on the outside contents of the layers.

Abstract: Known protective layers having high Cr content and additional silicon form brittle phases, which additionally become brittle under the effect of carbon during use. The protective layer according to the invention comprises a two-part metal layer, which contains tantalum on the outside.

Abstract: The invention relates to a novel alloy which comprises the elements carbon (C), chromium (Cr), cobalt (Co), molybdenum (Mo), tungsten (W), titanium (Ti), aluminium (Al), boron (B), and zirconium (Zr), based on nickel, and which has a very low tendency to form cracks during welding.

Abstract: A process is provided for forming an airfoil for a gas turbine engine involving: forming a casting of a gas turbine engine airfoil having a main wall and an interior cavity, the main wall having a wall thickness extending from an external surface of the outer wall to the interior cavity, an outer section of the main wall extending from a location between a base and a tip of the airfoil casting to the tip having a wall thickness greater than a final thickness. The process may further involve effecting movement, using a computer system, of a material removal apparatus and the casting relative to one another such that a layer of material is removed from the casting at one or more radial portions along the main wall of the casting.

Abstract: A process is provided for forming an airfoil for a gas turbine engine involving: forming a casting of a gas turbine engine airfoil having a main wall and an interior cavity, the main wall having a wall thickness extending from an external surface of the outer wall to the interior cavity, an outer section of the main wall extending from a location between a base and a tip of the airfoil casting to the tip having a wall thickness greater than a final thickness. The process may further involve effecting movement, using a computer system, of a material removal apparatus and the casting relative to one another such that a layer of material is removed from the casting at one or more radial portions along the main wall of the casting.

Abstract: A method for additive manufacturing with multiple materials. First (48), second (50), and third (52) adjacent powder layers are delivered onto a working surface (54A) in respective first (73), second (74), and third (75) area shapes of adjacent final materials (30, 44, 45) in a given section plane of a component (20). The first powder may be a structural metal delivered in the sectional shape of an airfoil substrate (30). The second powder may be a bond coat material delivered in a sectional shape of a bond coat (45) on the substrate. The third powder may be a thermal barrier ceramic delivered in a section shape of the thermal barrier coating (44). A particular laser intensity (69A, 69B) is applied to each layer to melt or to sinter the layer. Integrated interfaces (57, 77, 80) may be formed between adjacent layers by gradient material overlap and/or interleaving projections.

Abstract: By means of laser triangulation measurements of an uncoated and a coated component having holes, the exact positions of the holes can be detected for reopening after coating. A method for the surface analysis of at least partially closed holes which are to be opened is provided. A process for reopening coated holes is also provided.

Abstract: A method is provided for treating turbine blades having holes for discharging cooling air. A protective layer is provided and then the holes that are partly or completely closed by the protective layer are opened again. Coordinates concerning the position of the holes are acquired before the protective layer is applied using a laser triangulation sensor using a light source generating a light beam and a light detector. The data obtained is used after application of the protective layer to control a removal device for removing protective layer partly or wholly covering the holes. Each hole is measured by the light beam being shone into the hole in different positions in relation to the longitudinal mid-axis of the latter. The light beam is shone into the respective hole in a plane at at least three different angles to the longitudinal mid-axis thereof.

Abstract: A process for determining the position of closed holes in a component is provided. By carrying out laser triangulation measurements on an uncoated component and a coated component with holes, the exact position of the holes to be reopened may be detected following the coating. A device used to carry out this process is also provided.

Abstract: A process for determining the position of closed holes in a component is provided. By carrying out laser triangulation measurements on an uncoated component and a coated component with holes, the exact position of the holes to be reopened may be detected following the coating. A device used to carry out this process is also provided.

Abstract: A method for determining the layer thickness of a component to be coated is provided. The monitoring of the process is automated by carrying out laser triangulation measurement before and after the coating of the component. At least one reference point on the component is used to determine the distortion of the blade or vane. A device for carrying out the method is also provided.

Abstract: A process of electrical discharge machining using a wire electrode is provided. The use of a thick wire electrode means that the surface can be machined considerably more accurately. The wire electrode has a diameter of at least 2.0 mm. In a first step for machining the surface, a rough contour is produced on the component.