Abstract: Disclosed is a method for monitoring a generative fabrication process in which a component is formed in an installation space from a multiplicity of layers by using a three-dimensional data model and a following layer is fixed to a preceding layer by means of a high-energy beam. The method comprises detecting the component at least optically and detecting the installation space thermally during layer application. Also disclosed is a device for carrying out the method.

Abstract: The present invention relates to a sealing element (100) of an axial turbomachine for the sealing of regions at or in at least two static components of the turbomachine, wherein the components can be moved axially relative to one another. The sealing element (100) has a first radial region (1) with a first stiffness or rigidity and a second radial region (5) with a second stiffness or rigidity, wherein the first stiffness and the second stiffness are different from one another, and the sealing element (100) is configured as segmented in the peripheral direction of the turbomachine.

Abstract: An apparatus and method for the generative production of a component includes a movably dispensing structure for the disposal of a starting material layer; a bonding device, such as a laser, for the local bonding of this starting material layer to a cross section of the component being produced; a platform for supporting the component being produced, which can be displaced counter to a direction of layer buildup in a motor-driven manner; a position sensing device for sensing a position or change in position, such as vibration, of the platform in the direction of layer buildup with the capability of sensing interference as to whether the movement of the dispensing structure is not free of interference on the basis of the sensed position or change in position.

Abstract: The invention relates to a mid-frame (10) for a gas turbine, having at least one outer casing element (24), having at least one hub element (26) arranged on the inside of the outer casing element (24) in the radial direction, having a least one strut (42) by means of which the outer casing element (24) is connected to the hub element (26), and having at least one fairing element (46) that delimits at least partially a duct (44) at least in the radial direction, through which a gas can flow, and is constructed separately from the casing element (46), said fairing element having a passage opening (48), through which the strut (42) passes, for at least partial cladding of the strut on the outer peripheral side, wherein the fairing element (46) is coupled exclusively to the hub element (26), at least in the radial direction.

Abstract: Disclosed is a method for repairing a receiving hook for guide vanes, wherein the receiving hook is arranged in a housing of a turbomachine. The method comprises removing first material in a region of the receiving hook, which region extends over the circumference of the housing and thereafter applying second material in or on a region which extends over the circumference of the housing. The application of second material is performed using localized heat.

Abstract: A guide blade for a gas turbine is disclosed. The guide blade includes a blade leaf having a receptacle in which at least one sealing element is arranged, where the sealing element is movable relative to the blade leaf between a sealing setting, in which the sealing element is at least partially moved out of the receptacle, and a storage setting, in which the sealing element is moved back into the receptacle. The guide blade further includes at least one fluid channel by which fluid under pressure can be routed into the receptacle in order to move the sealing element from the storage setting into the sealing setting. An inlet opening of the fluid channel is formed on a pressure-side surface of the blade leaf. A housing as well as a gas turbine having at least one guide blade is also disclosed.

Abstract: Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip.

Abstract: The invention relates to a method for joining at least two rotor elements of at least one rotor of a turbomachine. The detecting of a radial runout of at least one radially outer-lying cylindrical surface of the rotor elements at each of at least two points that are spaced axially apart from each other occurs by a measuring device. Depending on this, a relative mounting alignment of the rotor elements with respect to one another, at which the distance of the total center of mass of the rotor is minimized relative to its total axis of rotation, is determined. The invention detects of the radial runout of the radially outer-lying cylindrical surfaces of the rotor elements occurs optically by at least one optical sensor element of the measuring device. The invention further relates to a measuring apparatus and to a mounting apparatus.

Abstract: A method for operating a system for a thermodynamic cycle with a multi-flow evaporator having at least two evaporator flow channels, wherein the evaporator flow channels are made to approximate each other with respect to at least one operating parameter of the individual evaporator flow channels, and/or wherein a pressure drop across the evaporator is automatically controlled.

Abstract: The seal arrangement for a mid turbine frame of a gas turbine, especially an aircraft gas turbine, includes a tubular fluid duct, especially an oil duct, which extends along an axial direction, a bearing sleeve surrounding the fluid duct radially outside and in the peripheral direction, and at least one seal ring arranged between fluid duct and bearing sleeve in the radial direction, this ring being arranged around the fluid duct. The seal ring is taken up at least partly in a groove provided in the bearing sleeve.

Abstract: Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system.

Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

Abstract: An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

Abstract: A method and device for partially masking a component or assembly during a coating process, the device including at least one masking plate for separating a region to be coated from a region to be masked, the masking plate having at least a portion of at least one opening which conforms closely to the contour of the component and is adapted to allow passage of the component therethrough is provided. In masked region, a gap is present along opening, at least one sealing element being disposed at the gap on the side of the masked region.

Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.

Abstract: A method for operating an internal combustion engine having a motor with cylinder and an injection system having a common rail and injectors for the cylinders. Each injector has an accumulator for holding fuel from the common rail. A multiple injection of fuel is performed during each working cycle of a cylinder, including injecting a first amount in a first injection and injecting a second amount in a second injection, and determining fuel pressure for the common rail and/or the accumulator. A fuel injection amount parameter is determined for the first injection; an individual accumulator pressure and/or a common rail pressure is determined for the second injection; and a fuel injection amount parameter is determined for the second injection. The individual accumulator pressure and/or the common rail pressure are/is considered for determining the injection amount parameter of the fuel for the second injection.

Abstract: In a quantity limiting valve for a fuel injection system of an internal combustion engine including a cylinder with an inflow region and an outflow region separated by a piston axially movably disposed in the cylinder and a flow limiting fluid flow path extending along the piston between the inflow and outflow regions wherein the piston is biased with its front surface into contact with a stop element, the contact area between the front surface and the stop surface includes between the piston and the stop element a contact structure providing for an intermediate space which is in communication with the inflow region thereby to expose the front surface of the piston to the pressure of the fluid in the inflow region.

Abstract: A method for controlling the speed of an internal combustion engine and a speed control circuit for carrying out the method. For controlling, fuel energy is used as an output variable. The control units are calculated in accordance with a stationary proportion gain which is calculated proportionally to the fuel energy and inversely proportional to the engine speed.

Abstract: The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Abstract: A method for the injector-specific diagnosis of a fuel injection device of an internal combustion engine, including the following steps: detecting a pressure progression in an individual accumulator of an injector in a time-resolved manner; evaluating the detected pressure progression; determining if there is a fault state of the injection device in the region of the injector on the basis of the detected and evaluated pressure progression; and identifying the fault state on the basis of the detected and evaluated pressure progression.