Abstract: A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.

Abstract: A sealing device for an integrally bladed rotor basic body of a turbomachine to suppress a gas exchange between a hot gas stream and a cooling air stream in the radial direction in contact areas of adjacent moving blades, including a plurality of sealing elements activatable by centrifugal force, which may be situated in the area of channels which extend from a high-pressure side to a low-pressure side and are peripherally delimited by the moving blades, an integrally bladed rotor basic body having such a sealing device, and a turbomachine having such an integrally bladed rotor basic body.

Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.

Abstract: A method for producing an integrally bladed rotor, in particular a gas turbine rotor, comprises the following steps:—Providing a blade (12) having a lower blade foot that has a joining surface (18);—Retaining the blade (12) in a retaining unit (20); and—Exciting the blade (12) to oscillate about an axis of rotation. A device for carrying out the method comprises a retaining unit, in which blade (12) can be solidly clamped in place, and an oscillating unit (24) that transmits translational oscillations to the retaining unit in a plane substantially parallel to joining surface (18), and a fixation unit (30) for establishing the axis of rotation.

Abstract: A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process.

Abstract: A method for fusion welding a metal workpiece, which has a monocrystalline structure, to a metal workpiece, which has a polycrystalline structure, using a fiber laser and producing an I seam, is disclosed. A rotor produced according to the method is also disclosed.

Abstract: A method of forming integrally bladed rotors for gas turbines is described. The method includes drilling in a workpiece material recesses defining flow passages and rotor blades, performing a coarse milling step to refine surfaces of the rotor blades, and filling the recesses between the rotor blades with a damping material, thus encasing the rotor blades in the damping material. The method further includes performing a finishing milling step to remove the damping material and the workpiece material on surfaces of the rotor blades, while maximizing a damping effect of the damping material on the rotor blades. To maximize the damping effect, the finishing milling tool moves along a path that preferentially mills one surface of a blade while the other surface is in contact with the damping material.

Abstract: In a method for producing an inlet coating (21) on a surface of a turbomachine (10), an electric arc (37) is produced between a first electrode (31) having a first material and a second electrode (32) having a second material. A gas stream (42) is produced through the electric arc (37) onto the surface, which entrains the first material and the second material from the electric arc (37) and deposits them on the surface to form the inlet coating (21) or a precursor layer (22) of the inlet coating (21).

Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Abstract: A planetary gear train is described which includes a sun gear, three or more planet gears, an annulus as well as a planet gear carrier, whereby the input is provided via the sun gear and the output is provided via the annulus or via the planet gear carrier, whereby each planet gear is mounted on both sides in a roller bearing, and whereby the planet gear carrier includes two axially spaced bearing washers as well as at least three webs that connect the bearing washers. Each roller bearing is configured as a single-row or multi-row cylindrical roller bearing, each planet gear has a flexurally elastic axis projecting axially on both sides beyond the gear body of the planet gear, and the connection between each roller bearing and the appertaining axis is configured to be spherically moveable.

Abstract: 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.

Abstract: A method for spraying a coating and a cold gas spray nozzle is disclosed. The method includes spraying a coating by the cold gas spray nozzle. A rinsing gas is fed to the cold gas spray nozzle during an interruption of the spraying or at an end of the spraying. Deposits in the cold gas spray nozzle are cooled and detached by the rinsing gas.

Abstract: A coupling element 2, 52 is disclosed for arrangement between shrouds 14,16 of adjacent rotor blades 4, 6, the coupling element having force-transmission surfaces 28, 30 for bounding damping gaps 12a, 12b between shrouds 14, 16, and a rotor having at least one coupling element 2, 52 of this type.

Abstract: A method for producing an integrally bladed rotor, in particular a gas turbine rotor, by means of joining, comprises the following steps:—Providing a blade (10) having a joining surface;—Providing a retaining mechanism having two clamping jaws (28);—Retaining the blade (10) at two opposite points of blade (10) by means of clamping jaws (28) in a purely force-closed manner; and—Pressing the blade (10) retained in a force-closed manner onto a basic rotor body, so that blade (10) is aligned independently in a joining position. A device for producing an integrally bladed rotor comprises a retaining mechanism for a blade (10) having two clamping jaws (28), and by pressing these jaws together, blade (10) is retained at two opposite points in a purely force-closed manner; and a mechanism for pressing blade (10) retained in a force-closed manner onto a basic rotor body, in such a way that blade (10) is aligned independently in a joining position.

Abstract: The invention relates to a method for producing a component (10) of a turbomachine, especially a structural part of a turbine or a compressor, the method being a generative production method for the layer-by-layer buildup of the component (10). After production of one or more successive component layers pressure is applied to at least sections of the surface of the most recently produced component layer (12), the pressure being induced by laser or plasma. The invention further relates to a device for producing a component (10) of a turbomachine, especially a structural part of a turbine or a compressor, the device (26) comprising at least one powder feed (28) for the deposition of at least one powder component material (16) onto a component platform, at least one radiation source (14) for a local layer-by-layer fusion or sintering of the component material (16) and at least one laser radiation source (20) or at least one plasma impulse source.

Abstract: The invention relates to a method for producing a component (12), especially a hollow structural part for a turbomachine. The method is characterized by the following steps: a) layer-by-layer deposition of at least one powder component material (20a) onto a component platform in the region of a buildup and joining zone (I), b) deposition of at least one liquid component material (20b) onto the powder component material (20a), the liquid component material (20b) comprising at least one metal-containing compound, c) local layer-by-layer fusion or sintering of the component materials (20a, 20b) by means of thermal and/or electromagnetic energy supplied in the region of the buildup and joining zone (I), d) lowering of the component platform by a predefined layer thickness; and e) repetition of steps a) to d) until the component (12) is finished. The invention further relates to a device (10) for producing a component (12) of a turbomachine, especially a hollow structural part for a turbomachine.

Abstract: 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.

Abstract: A device (2) having at least one connecting element (24, 26) for fastening a component (4) to, respectively for detaching it from a component carrier (6) using adhesive bonds; a mechanical peeling device (8) being provided for breaking the adhesive bonds. Also a method for fastening a component (4) to, respectively for detaching it from a component carrier (6).

Abstract: A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: The invention relates to a method for producing a rotor or stator blade (1a) of a gas turbine, in particular an aircraft gas turbine (2), comprising forming a airfoil (8a) made of at least one first material and attaching a blade root (4a) made of at least one second material to the airfoil (8a) by means of a thermal spraying method. The invention further relates to a rotor or stator blade (1a) produced according to such a method.