Abstract: A low-pressure turbine of a gas turbine is disclosed. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades. Each stage is characterized by a characteristic value vane-to-blade ratio that indicates the ratio of the number of vanes to the number of blades within a stage. One of the stages of the turbine is designed in such a manner that, in the event of noise-critical conditions of the turbine, the characteristic value vane-to-blade ratio of this stage is between a lower cut-off limit for mode k=?1 of the blade-passing frequency (BPF) of said stage and an upper cut-off limit for the mode k=?2 of the blade-passing frequency (BPF) of this stage.

Abstract: A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.

Abstract: A compressor, particularly a high-pressure compressor, of a gas turbine, particularly of an aircraft engine, includes at least one rotor and a number of blades (11, 12), which are assigned to the or to each rotor and which rotate together with the respective rotor. Each blade (11, 12) is delimited, in essence, by a flow entry edge or leading edge (16), a flow exit edge or trailing edge (17), and by a blade surface (20), which extends between the leading edge (16) and the trailing edge (17) while forming a suction side (18) and a pressure side. The leading edges (16) of the blades (11, 12) are slanted at a sweep angle that changes with the height of the respective blade (11, 12) in such a manner that the leading edges (16) comprise, in a radially external area (23) of the same, at least one forward sweep angle, a backward sweep angle or zero-sweep angle following in a radially external manner, and a forward sweep angle following, in a radially external manner, the backward sweep angle or the zero-sweep angle.

Abstract: A rotor of a turbo machine having a rotor base and a plurality of rotor blades. Each rotor blade is anchored in an axial groove of the rotor base body via the blade footing and the rotor blades are secured in the rotor base body by locking plates which are guided in ring grooves of the rotor base body and the rotor blades. The locking plates have a diamond-shaped outline, in particular in the form of a parallelogram or a rhombus such that in an insertion position, the locking plates can be inserted between the rotor base body and the rotor blades, and in an installation position, which is rotated with respect to this insertion position, they can be rotated into the ring grooves of the rotor base body and the rotor blades.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally bladed, circumferentially closed rotor blade ring. The rotor blades, or rotor blade segments, or rotor blade ring are/is anchored in the groove extending in the circumferential direction of the rotor base body by a blade base or ring base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments, or ring base of the rotor blade ring, being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A rotary friction welding machine and method is disclosed. The rotary friction welding machine has a first rotating spindle and a second non-rotating spindle, where a first component of the components being connected to one another is positioned on the first spindle and a second component of the components being connected to one another is positioned on the second spindle. Several flywheel mass bodies are positioned on the rotary friction welding machine, where the flywheel mass bodies cooperate with the first rotating spindle such that at least one of these flywheel mass bodies can be brought out of operating engagement or into operating engagement with the first rotating spindle, where both the flywheel mass bodies that are in operating engagement with the first rotating spindle and the flywheel mass bodies that are out of operating engagement with the first rotating spindle are positioned on the rotary friction welding machine.

Abstract: A rotor for a turbo machine, in particular for a gas turbine, is disclosed. The rotor includes a rotor base body and several rotor blades arranged over the circumference of the rotor base body, in which case the rotor base body is manufactured of an MMC composite material, and in which case the rotor blades are an integral part of the rotor. The rotor base body is configured in the shape of a ring, in which case the ring-shaped rotor base body includes, in a radially internal section, at least one groove-like recess which is filled radially on the inside with fibers exhibiting tensile strength.

Abstract: A seal arrangement for a gas turbine is disclosed. The seal arrangement is used for sealing a gap between radially internally located ends of guide vanes of a guide vane ring and a rotor, in which case the rotor has at least two seal projections positioned at an axial distance relative to each other in a circumferential direction of the rotor. The seal projections effecting a seal of the gap in combination with intake linings associated with the radially internally located ends of the guide vanes. The seal projections are inclined or tilted in the axial direction toward a side of higher pressure, where, in a space limited by the minimum of two seal projections and the corresponding intake linings, at least one recirculation structure is provided. The recirculation structure, or each recirculation structure, is oriented toward the side of the higher pressure.

Abstract: The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass flow flows. The mixing tube is designed in the form of a truncated cone narrowing in the direction of flow and has openings arranged at the downstream end in the circumferential direction of the mixing-tube lateral surface in a cross-sectional plane lying perpendicularly to the longitudinal axis of the mixing tube. The hot core stream flowing through the mixing tube penetrates through the openings into the cold bypass flow flowing around the mixing-tube lateral surface. The openings have passage areas of elliptical shape with a major axis and a minor axis, the major axis of the passage areas running on the lateral surface of the mixing tube in the direction of flow of the fluids and the minor axis running perpendicularly thereto.

Abstract: A method and apparatus for coating a workpiece is disclosed. A material is applied to the workpiece by thermal spray coating. The spraying process is monitored on-line by detecting properties of the particles in the spray jet and supplying them as actual values, where the actual values are compared directly with target values, or characteristic quantities derived from the actual values are compared with the target values and, when a deviation is found between the actual values or characteristic quantities and the pre-specified target values, the process parameters for thermal spray coating are automatically adjusted by a regulator on the basis of a neuronal network.

Abstract: A process for gas diffusion coating of metallic components; in which a component surface which is to be coated is brought into contact with a metal halide as coating gas, to form a diffusion layer with a defined layer thickness and a defined coating metal content in % by weight in the component surface, working on the basis of a nominal concentration of the metal halide at the component surface which, at a defined coating temperature, leads to a defined coating time, wherein a first concentration, which is higher than the nominal concentration, for the metal halide is established for a first time, and at least one second concentration, which is at or below the nominal concentration, is established at the component surface for at least one second time, the first and the at least one second time being selected in such a way that their sum is shorter than the coating time with the nominal concentration. Also disclosed is a device for the process.

Abstract: The invention relates to a rotor (10) for a power plant, in particular an aero engine or a gas turbine, whereby said rotor (10) comprises at least two bonded rotor discs (12, 14). The rotor (10) is characterised in that an inlet opening (30) for inlet of fluid from around the rotor (10) into a chamber (26, 44) in one or between two adjacent rotor discs (12, 14) is provided and at least one interrupter element (38) with at least one fluid passage (40) is arranged in the chamber (26).

Abstract: A sealing arrangement, especially for a flow engine, for non-hermetically sealing a gap (12) between a rotor (10) and a stator (11), which comprises a seal having a plurality of sealing elements that are fixed to a sealing element support, said sealing element support being at least partially disposed in a receptacle (16) which is defined by a supporting element (17) and a cover element (18) is disclosed. The sealing element support is configured as a ring that is interrupted once or several times. Free ends (19, 20) of the sealing element support overlap in the area of interruptions in the circumferential direction. The contours of the supporting element (17) and the cover element (18) are adapted to the contours of the sealing element support and the sealing elements (15). At least one end (19, 20) of every part of the sealing element support is associated with an anti-twist stop (21, 22).

Abstract: A fiber laminate is provided, as well as a method for producing the fiber laminate and a method for making a component from the fiber laminate. The fiber laminate includes several fiber layers having reinforcement fibers extending in a preferential direction, and/or several multiaxial nonwoven fabrics consisting of reinforcement fibers, of various contours, wherein the fiber layers are fixed one under the other and/or placed in the multiaxial nonwoven one on top of the other along at least one area before contouring.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades or rotor blade segments. The rotor blades or rotor blade segments are each anchored in the groove extending in the circumferential direction of the rotor base body by a blade base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A method and apparatus for the detection of flaws, in particular of fissures, in metal components, is disclosed. A pulsed high-frequency magnetic field is coupled to the component. The temperature distribution of thermal energy generated by eddy currents during the application of a magnetic field pulse is detected.

Abstract: In a transverse flux machine, the rotor has multiple permanent magnet rings that are arranged axially in proximity to one another. The stator surrounds the rotor concentrically in at least some sections, forming an air gap. The stator has multiple stator coils oriented coaxially with the permanent magnet rings and the stator coil has two terminals. An active reactive power source to be controlled has two terminals for each stator coil, the respective stator coil being connected to each. In the event of a fault incident in one of the stator coils, a monitoring arrangement supplies triggering signals for the active reactive power source so that the two terminals of the respective stator coil are interconnected with a low resistance.

Abstract: A gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade and a vane footing. The blade is defined by a flow inlet edge or a front edge, a flow outlet edge or a rear edge, and a blade surface extending between the front edge and the rear edge and forming a suction side and a pressure side. The suction side of the blade includes at least one microprofiled or microstructured region for optimizing the flow around the blade.

Abstract: The invention relates to a rotor for a turbomachine, in particular a low-pressure turbine rotor for a gas turbine, having at least one stage, each stage comprising a rotor disk having rotor blades attached to the rotor disk, and the rotor disk of each stage being removably connected either to oppositely situated rotor disks of adjoining stages or to a rotor connection of a rotor shaft by at least one respective attachments. According to the invention, the, or each of the, attachment means extends through the rotor disk of at least one stage, whereby the, or each of the, attachment means is guided with radial play into at least one borehole passing through the respective rotor disk, so that an interior borehole surface is not subjected to load or force.

Abstract: A turbocompressor flow structure comprises a ring chamber which is arranged concentrically to an axis of a turbocompressor in an area of free blade/vane ends of a rotor blade ring/vane ring and is adjacent radially to a main flow channel. A ring chamber is provided which is bordered by a front upstream wall, a rear downstream wall and a wall that runs essentially axially. Baffle elements are arranged in the ring chamber and the ring chamber permits flow penetration in a circumferential direction in a front and/or rear area. At least one opening is provided in the area of the wall that runs essentially axially or in the area of the upstream wall and permits flow penetration out of the ring chamber, at least one compressor chamber being provided to accommodate this outgoing flow.