Abstract: An air scoop-cyclone filter assembly having an air scoop for guiding untreated air, which including an inlet opening, a deflection area for deflecting untreated air and an outlet opening, and having a cyclone filter for cleaning untreated air, which is connected downstream of the air scoop in the flow direction and is connected in an airtight manner to the air scoop A perforated plate is arranged in the cyclone filter as a filter inlet opening. The perforated plate has a first passage area having a high number of holes, a second passage area having a low number of holes at the geodetically deepest point, and a baffle plate. The baffle plate distributes the untreated air flow through the first and second passage area and, with the outer wall of the air scoop, forms a collecting chamber that stabilizes the flow.

Abstract: A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity between a rim of at least one of the disks and the shaft and at least one aft cavity formed between a rim of at least one other of the disks and the shaft; a first flow of cooling air in the at least one forward cavity; and a second flow of cooling air in the at least one aft cavity.

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: A method for correcting a fuel quantity injected by a fuel injection device during operation of an internal combustion engine, including: determining an air heat characteristic variable, on which an air heat stream fed to a combustion chamber of the engine functionally depends; determining an exhaust heat characteristic variable, on which an exhaust heat stream discharged from the combustion chamber functionally depends; determining a heat distribution factor, which specifies a fraction of the exhaust heat stream reduced by the air heat stream in relation to a heat stream fed with the injected fuel to the combustion chamber; calculating a fuel mass fed to the engine from the air heat characteristic variable, the exhaust heat characteristic variable and the heat distribution factor; calculating a comparison variable by comparing the calculated fuel mass with a fuel mass setpoint value and adapting actuation of the fuel injection device depending on the comparison variable.

Abstract: A brush seal system for sealing a clearance between components of a turbo engine that are movable in relation to one another, in particular of a thermal gas turbine, is disclosed. The brush seal system includes a brush seal housing, which accommodates at least one brush head of a brush seal, where the brush seal housing includes a first component having a cover plate section and a second component having a support plate section. The first component includes an axial flange forming a fish mouth seal on an end opposite the cover plate section. A thermal gas turbine having such a brush seal system is also disclosed.

Abstract: A method for venting a fuel supply line of a direct-injection internal combustion engine, wherein the fuel supply line has an injector, a high-pressure accumulator upstream of the injector, a flow rate limiting valve between the high-pressure accumulator and the injector for the purposes of limiting a fuel flow rate passing from the high-pressure accumulator to the injector, and a high-pressure pump upstream of the high-pressure accumulator for delivering fuel into the high-pressure accumulator. A pressure in the high-pressure accumulator is regulated by an intake throttle arranged upstream. of the high-pressure pump. In this case, it is provided that the fuel supply line is vented downstream of the high-pressure pump, wherein, during venting operating mode, a passage cross section for the fuel which is smaller than or equal to a predetermined threshold passage cross section is set in the intake throttle.

Abstract: A method for operating an internal combustion engine having at least one fuel injection valve for introducing fuel into a combustion chamber of the internal combustion engine, the valve being supplied with a specified current intensity in order to adjust a specified flow cross-section of a fuel fluidic connection in the combustion chamber. The maximum specified current intensity during normal operation is equal to a first current intensity and during a release operation is equal to a second, higher current intensity.

Abstract: A method for cleaning a combustion chamber of an internal combustion engine, having the following steps: introducing a gaseous substance into a cooling device, wherein the gaseous substance has, at least upstream of the cooling device, a relative humidity of greater than 0%; cooling the substance in the cooling device to below a dewpoint, such that water precipitate is formed; introducing the substance and the precipitate into a combustion chamber of the internal combustion engine; performing a combustion reaction in the combustion chamber; and discharging residues from the combustion chamber.

Abstract: A method and an arrangement for operating an internal combustion engine. In the method, an injection start is calculated by a filter, starting from a standard injection start and at least one of the filter parameters is selected in accordance with the operating mode of the internal combustion engine.

Abstract: Intake manifold element (1) having a tubular section (3) through which a first fluid (A) can flow in a proposed flow direction (A?) via a flow channel (4) from an inlet (4a) to an outlet (4b) of the same, said tubular section being provided for arrangement on a compressor inlet (11a) of a turbocharger, characterized in that the flow channel (4) has a nozzle-shaped design, wherein its cross-section which the fluid can flow through is tapered in the flow direction (A?), wherein the tubular section (3) forms a chamber (6) adjacent to the nozzle-shaped flow channel (4) which serves as flow path from an inlet (6a) to an outlet (6b) for the aspiration of a second fluid (B), the pressure level of said chamber on the inlet (6a) being dependent on the pressure level of the first fluid (A) on the outlet (4b) of the flow channel (4) via communicating outlets (6b, 4b) of the chamber (6) and the flow channel (4).

Abstract: A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating.

Abstract: A method for operating a traction vehicle, especially a locomotive, wherein the power delivered by a drive system is produced by at least two internal combustion engines, each of which is functionally connected to a generator for producing electric power, the engines preferably being gas engines, even more preferably lean gas engines. A previously determined number of separate power stages ranging from a minimum power up to a nominal power of the drive system is provided. The interval between all directly adjacent power stages is selected so that it corresponds to a constant fraction of the nominal power of the drive system.

Abstract: A control and regulation method is described for a turbocharged internal combustion engine, in which in a high-performance range (HLB) the turbocharged air is pre-compressed via a two-stage turbocharging process. The described method comprises a low-pressure stage and a high-pressure stage and fed to the internal combustion engine and in which in a low-performance range (NLB) the turbocharged air, pre-compressed via the two-stage turbocharging process, is fed to the internal combustion engine, post-compressed via a compressor as a third turbocharging stage.

Abstract: A gas turbine jet engine having a main flow channel and a housing structure which radially surrounds this main flow channel. A housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly. The flow of the housing gas flow to and/or along the main flow channel may be adjusted by adjusting a flow conducting sheet.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.

Abstract: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).

Abstract: A device for generative production of at least one component area of a component, in particular a component of a turbine or a compressor, is disclosed. The device includes at least one powder feed for application of at least one powder layer to a build-up and joining zone of a component platform that can be lowered and at least one radiation source for generating at least one high-energy beam by which the powder layer can be fused and/or sintered locally in the area of the build-up and joining zone to form a component layer. The device further includes a camera system which can produce at least one stereoscopic image for three-dimensional detection of at least one area of the component layer. A method for producing at least one component region of a component, in particular a component of a turbine or a compressor, is also disclosed.

Abstract: The invention relates to a supply system for a medium, in particular for an exhaust-gas purification apparatus for the treatment of exhaust gases of an internal combustion engine, having a storage vessel for the medium, having a dosing device for dosing the medium, and having a provision line which comprises a feed line for the supply of the medium to the dosing device and a return line for returning the medium from the dosing device into the storage vessel. Flow can pass through the dosing device from a feed port to a return port of the dosing device. The provision line comprises an additional fluid connection between the feed line and the return line. The additional fluid connection opens out into the feed line upstream of the feed port of the dosing device and opens out into the return line downstream of the return port of the dosing device.

Abstract: A carrier housing for a turbocharger arrangement to be fastened at an internal combustion engine includes first, second and third fastening flanges for fastening to turbines of a respective one of a high-pressure turbocharger, a first low-pressure turbocharger, and a second low-pressure turbocharger. The carrier housing is configured such that exhaust can be guided to the turbines of the high-pressure turbocharger, the first low-pressure turbocharger and the second low-pressure turbocharger via a respective one of the first, second and third fastening flanges. The carrier housing includes at least one connection flange by which the fastening flanges are directly in a fluid-guiding connection, with the connection flange being further connected to an exhaust guidance such that exhaust flows from the internal combustion engine through the first and second connection flanges and directly to the carrier housing.

Abstract: The invention relates to a V engine, especially a diesel engine, comprising a first cylinder bank and a second cylinder bank, said V engine being designed for two-stage charging by means of a low-pressure exhaust gas turbocharger and a high-pressure exhaust gas turbocharger. The invention is characterized in that the low-pressure exhaust gas turbocharger and the high-pressure exhaust gas turbocharger are respectively arranged on the front of a cylinder bank above a main output element of the V engine.