Abstract: A guide system for repairing turbomachinery includes a housing; a guide tube have a hollow interior for accepting a working tool module; an axial motor for moving the guide tube axially with respect to the housing; a rotational motor for rotating the guide tube with respect to the housing; and an attachment for securing the housing with respect to a turbomachinery casing. A repair kit and method are also provided.

Abstract: A cooling system for cooling a turbine blade with a cooling fluid via an internal flow passage formed in the turbine blade extending from an inlet to an outlet edge having a first passage section defining a first flow direction, a second passage section defining a second flow direction, a wall between the first and second passage section and a diverter, between the first and the second passage section. The wall in a region of the diverter forms a pier head which extends into the region of the first passage section and thereby reduces the flow cross section of the flow passage.

Abstract: A belt-tensioning device, in particular for an internal combustion engine, the belt-tensioning device including a bearing housing having a latching recess, a tensioning roller, a pivoting arm and a locking device. The pivoting arm is mounted on the bearing housing, the pivoting arm being under a torsion spring load. The tensioning roller being coupled to the pivoting arm. The locking device having a first latching device and a second latching device. The first latching device and the second latching device being coupled with the pivoting arm. The latching recess interacts with at least one of the first latching device and the second latching device wherein the locking device is configured in such a way that the pivoting arm can be locked by the locking device in different predefined latching positions and the pivoting arm can be pivoted with predefined freedom in an operating position.

Abstract: A device and a method for producing a blade airfoil from a workpiece which comprises at least two gaps and at least one blank arranged between the two gaps, wherein the blank comprises two opposite lateral faces which are bounded by a base, a top and a first and a second edge. The method comprises: (a) arranging the first and second electrodes in the first and second gaps, the surface of the workpiece forming an annular space surface at the gaps, (b) applying a positive voltage to the blank and applying a negative voltage to the first and second electrodes, (c) moving the first and second electrode in the direction of the first and second lateral faces. Step (b) is preceded by passing electrolyte between the two electrodes over the top toward the base.

Abstract: An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

Abstract: A gas turbine component for a gas turbine is provided. The gas turbine component has a shell portion having an abradable portion (2) to allow rotor blade ends (1) of a rotor blade array of the gas turbine to rub into the same. The abradable portion adjoins a neighboring portion (3) of the shell portion axially at both sides and is additively manufactured together therewith.

Abstract: The present invention relates to a guide vane, in particular an outlet guide vane and/or a guide vane for a compressor stage of a gas turbine, wherein the vane has a vane blade with a first vane blade portion and a second vane blade portion, and the first vane blade portion can be reversibly rotated in relation to the second vane blade portion about an axis of rotation from a first position to a second position, wherein, in at least one profile portion of the vane blade, the axis of rotation is arranged outside of a profile of the first vane blade portion, and/or a profile of the first vane blade portion has a suction side with a first contour portion and a second contour portion, which, in particular, is adjoined thereto, and a profile of the second vane blade portion has a pressure-side contour portion.

Abstract: A method for operating an internal combustion engine with a high pressure accumulator for a fuel injection system, includes the steps of: monitoring, in a time-dependent manner, a high pressure in the fuel injection system; conducting a check, at a high pressure-dependent starting time point, as to whether a continuous injection detection is to be carried out; and checking whether a high-pressure oscillation has occurred within an oscillation time interval prior to a starting time.

Abstract: A method for manufacturing a blade or vane assembly having at least one hollow airfoil (10) for a gas turbine, profile sections (A, B, C) of this airfoil being configured (S20) on the basis of a predetermined desired torsion of the airfoil, and the airfoil being manufactured (S30) on the basis of the configured profile sections using an additive manufacturing process (S30).

Abstract: The present invention relates to a method for manufacturing a plate of a turbomachine having a plurality of receiving grooves, which are formed on the cylindrical peripheral surface of the plate in order to receive blade roots of blades of the turbomachine. The receiving grooves extend in a straight line from one face of the plate to the other face of the plate, such that a straight line delimits the receiving groove from each point on the cross section of the receiving groove on one of the faces to the corresponding point on the cross section on the other face. A circular plate is provided and a plurality of receiving grooves are introduced into the plate simultaneously on opposing regions relative to a central axis of rotation of the plate.

Abstract: Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, a radially outer shroud, and an airfoil extending between the blade root and the shroud. It is provided that the outer shroud have only a single sealing element, which projects radially from the shroud, in particular only a single sealing fin.

Abstract: A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity ? is at least 10% lower than the specific thermal conductivity ? of air.

Abstract: A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle ? with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle ? with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus ??90°, in terms of absolute value, being >0° (|??90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus ??90°, in terms of absolute value, being >??90° (|??90°|>??90°).

Abstract: A blade arrangement for a turbomachine, in particular a gas turbine, with a first blade, which has a first blade body and a first platform, and a second blade, which is adjacent in the peripheral direction, and has a second blade body and a second platform. A first wall of the first blade and a second wall of the second blade bound a blade cavity, in which a damper with a wall-side contact surface is arranged. This contact surface has at least one first surface portion, which is convexly curved in a first direction, which, in at least one contact position, contacts the first wall in the first surface portion and is parallel to at least one portion of an edge of the first platform, said edge facing the second platform.

Abstract: A stator vane (3) for a turbine (50c) of a turbomachine (50), the stator vane having a stator vane airfoil (3c), an inner shroud (3a) and an outer shroud (3b), the inner shroud (3a) and the outer shroud (3b) bounding an annular space (2), in which working gas (51) is conveyed during operation, radially with respect to a longitudinal axis (52) of the turbomachine (50), and the stator vane airfoil (3c) having a stator vane airfoil channel (3d) extending through its interior between a radially inner inlet (6) and a radially outer outlet (7). A characteristic features is that the inlet (6) is disposed in such a manner that a gas (8) flowing through the stator vane airfoil channel (3d) during operation is at least partially formed of the working gas (51) conveyed in the annular space (2), and thus the working gas is redistributed from radially inward to radially outward.

Abstract: The invention relates to a method for carrying out maintenance work on a complex structural component, in particular, a gas turbine, by means of a virtual work environment. The virtual work environment has a display device and a computing device, said computing device being connected to a memory device, in which the characteristics of the complex structural component, together with its component parts and their assembly sequence, are stored. During the method, at least one component part needing maintenance, or a predefined modification state of the structural component is selected in the virtual work environment From this step, the disassembly or assembly steps required for disassembling the component parts of the structural component are calculated and displayed, in order to obtain access to the at least one component part needing maintenance, or to achieve the selected modification state.

Abstract: Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.

Abstract: A method for operating an internal combustion engine having an injection system which has a high-pressure accumulator, high pressure in the high-pressure accumulator being controlled via a suction throttle on the low-pressure side, acting as a first pressure control element in a first high-pressure control loop. During normal operation, a high-pressure disturbance variable is produced by a pressure regulating valve on the high-pressure side, acting as an additional pressure control element, via which fuel is re-directed from the high-pressure accumulator into a fuel reservoir, the at least one pressure regulating valve being controlled, during normal operation, based on a set volumetric flow rate for the fuel to be re-directed. A temporal development of the set volumetric rate is sensed and the set volumetric flow rate is filtered, a time constant for the filtering of the set volumetric flow rate being selected as a function of the sensed temporal development.

Abstract: A distributor apparatus of a common rail system for an internal combustion engine. The distributor apparatus is designed with at least one distributor device having a high-pressure line for fuel and a plurality of feed lines branching off from the high-pressure line within the distributor device. Each feed line leads to an individual accumulator and an injector. The feed line is associated with a restriction device and a discharge bore, which is designed to cooperate with a pressure-measuring device and which is arranged downstream of the restriction device, such that the restriction device is arranged in the feed line and the discharge bore, arranged in the distributor device, is connected to the feed line downstream of the restriction device.

Abstract: A method for operating an injection system of an internal combustion engine, including: providing the injection system includes a high pressure accumulator; regulating a high pressure in the high pressure accumulator in a normal operation by way actuating a low pressure-side suction throttle; regulating the high pressure in a first operating mode of safety operation by way of actuating at least one high pressure-side pressure control valve; carrying out a switchover from the normal operation into the first operating mode of safety operation if the high pressure reaches or exceeds a first limit pressure value; and carrying out a switchover from the first operating mode of safety operation into the normal operation if, starting from above a setpoint pressure value, the high pressure reaches or undershoots the setpoint pressure value, which is lower than the first limit pressure value.