Abstract: A radial compressor has a compressor housing, a rotatably supported compressor shaft in the compressor housing, at least one compressor impeller arranged on the compressor shaft, and a fluid discharge element arranged downstream of a last compressor impeller in a fluid path in the compressor housing and which has a predetermined extension in radial direction and in axial direction of the radial compressor, wherein the fluid discharge element has a fluid passage for guiding fluid that is accelerated by the last compressor impeller out of the compressor housing, which fluid passage extends in a circumferential direction by a predetermined angular amount, and wherein the fluid discharge element is formed of material having a defined material structure, and the fluid passage is formed as a subsequently introduced spatial interruption in a material cohesion of the material structure. A method of producing the radial compressor is also disclosed.

Abstract: A rotor wheel for a turbomachine, particularly a radial turbomachine, having a rotor wheel face and a shrink collar adjoining the rotor wheel face for shrinking onto a rotor of the turbomachine and a circumferential groove between the rotor wheel face and the shrink collar.

Abstract: A turbine includes a stator (10) and a rotor (20); a plurality of turbine stages (30) through which a flow path of an operating fluid extends; an axial thrust balancing piston (40) arranged at the rotor and a first piston chamber (41) connected to one of the turbine stages (30.1) so that the operating fluid can be conveyed into the first piston chamber with a first fluid pressure, and a second piston chamber (42) has a counterpressure so that an axial thrust opposed to a flow direction of the operating fluid can be exerted on the rotor; and a pressure control device (60) connected to the second piston chamber. The pressure control device constructed to vary the counterpressure by controlled removal of fluid from the second piston chamber so that the axial thrust of the axial thrust balancing piston can be varied.

Abstract: Turbomachine component and turbomachine outfitted therewith. The turbomachine component has a sensor unit arranged at the turbomachine component. The sensor unit has a sensor for detecting a parameter to be monitored and a transmitter for sending a measurement signal corresponding to the parameter to an evaluation unit of the turbomachine for processing. The transmitter of the sensor unit sends an encoded identification signal to the evaluation unit along with the measurement signal, this encoded identification signal contains an identification code that identifies the sensor unit. The sensor unit is configured such that the sensor unit cannot be separated from the turbomachine component without functional destruction of the sensor unit.

Abstract: A cooler for cooling a gaseous medium includes: a housing; a heat exchanger in the housing, the heat exchanger having an inlet portion at a flow inlet side of the heat exchanger, an outlet portion arranged at a flow outlet side of the heat exchanger, and tubes through which a coolant flows and about which gaseous medium to be cooled circulates; at least one inflow, through which the medium to be cooled can be introduced into the housing and fed to the inlet portion of the heat exchanger; at least one drain, through which cooled medium originating from the outlet portion of the heat exchanger can be discharged out of the housing; and at least one perforated plate-like flow homogenization element positioned in the housing at a position upstream of the inlet portion of the heat exchanger, seen in a flow direction of the medium to be cooled.

Abstract: Compressor arrangement having an axial compressor and a radial compressor which are arranged axially one behind the other on a common driveshaft which can be coupled to a drive and which each have a compression fluid input and a compression fluid output. The axial compressor is provided with first control elements and the radial compressor is provided with second control elements. The first control elements and second control elements are controllable separately so that the axial compressor and the radial compressor are controllable separately.

Abstract: An exhaust valve spindle for an exhaust valve in an internal combustion engine has a shaft and a valve disc at the lower end of the shaft, which valve disc at its upper surface has a seat area. The seat area is of a seat material comprising at least from 34.0 to 44.0% Cr, an aggregate amount of Nb and Ta in the range from at least 2.8 to 6.1%, from 0.3 to 2.0% Ti, at the most 0.2% Al, at the most 0.04% B, at the most 0.8% Fe, at the most 0.04% C, at the most 0.4% Si, and a balance of Ni, where the amount of Ti+Nb+0.5×Ta is in the range from 3.4 to 6.6%, and where the amount of Nb+0.5×Ta is less than 3.0% if the amount of Ti is larger than 1.5%.

Abstract: A cylinder head and internal combustion engine outfitted therewith, in which the cylinder head has a plurality of media passages, at least one of which is for conducting a corrosive medium. Each media passage has a media contact surface for conducting a medium. The cylinder head has a longer service life due to the media contact surface of the at least one media passage for conducting the corrosive medium being formed of a corrosion-resistant material.

Abstract: A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Abstract: An exhaust valve for an internal combustion engine comprises a valve disc having a first side (14) and a second side (16), a valve stem extending from the first side of the valve disc, and an annular valve seat area (11) located at the first side of the valve disc. The annular valve seat area (11) is of a nickel-base alloy or a chromium-base alloy and has a valve seat surface. The annular valve seat area has at least a first annular portion (43) located in between two second annular portions (42). The first annular portion has lower hardness than the two second annular portions.

Abstract: Combustor for a turbine having a housing in which an air collecting chamber, a combustion antechamber, and a combustion chamber are formed. A combustor head plate is arranged in the housing so that the combustor head plate separates the combustion antechamber from the combustion chamber. A baffle plate is arranged in the combustion antechamber so that the baffle plate divides the combustion antechamber into a first sub-chamber adjoining an air supply fluidically connected with the air collecting chamber and a second sub-chamber adjoining the combustor head plate. Wherein baffle plate has a plurality of through-passages that fluidically connect the first sub-chamber with the second sub-chamber so that air that has flowed into the first sub-chamber from the air collecting chamber via the air supply can flow into the second sub-chamber via the through-passages and to a back surface of the combustor head plate facing the second sub-chamber.

Abstract: Disclosed is a heat-insulating protective layer for a component located within the hot gas zone of a gas turbine. Said protective layer is composed of an adhesive layer, a diffusion layer, and a ceramic layer which is applied to the high temperature-resistant basic metal of the component. The adhesive layer comprises a metal alloy [MCrAlY (M=Ni, Co)] containing Ni, Co, Cr, Al, Y, the diffusion layer is produced by calorizing the adhesive layer, and the ceramic layer is composed of ZrO2 which is partially stabilized by means of yttrium oxide. One or several chemical metal elements that have a large atomic diameter and are selected among the group comprising Re, W, Si, Hf, and/or Ta are alloyed to the material of the adhesive layer. The adhesive layer has the following chemical composition after being applied: Co 15 to 30 percent, Cr 15 to 25 percent, Al 6 to 13 percent, Y 0.2 to 0.

Abstract: A solar thermal installation and method for operating a solar thermal installation includes a solar collector arrangement which defines a solar collector fluid passage so that a first heat quantity can be supplied to a fluid, and which has a first fluid infeed connection and a first fluid output connection. A heat exchanger fluid passage permits a second heat quantity to be supplied to a fluid. A heating fluid receiving device is fluidically connected with a first fluid output connection and fluidically connects a second fluid output connection to the first fluid output connection by bypassing the solar collector fluid passage. A consumer device is connected to the heating fluid receiving device. At least a portion of the first heat quantity and second heat quantity can be supplied to the consumer device. A control device controls an operation of the gas turbine depending on the first heat quantity.

Abstract: Rotor having of rotor blades. Every rotor blade has a blade body and coupling segment. A width of the coupling element segment is defined in circumferential direction by edges extending in axial direction. The coupling segment is contoured at a first side such that, on the flow inlet side to a flow inlet edge, the radially outer edge projects beyond the radially inner edge in axial direction. At this side on the flow outlet side of the blade body, the radially inner edge projects beyond the radially outer edge. The coupling segment is contoured at a second side such that, adjacent on the flow outlet side to the flow outlet edge, the radially outer edge extending in axial direction projects beyond the radially inner edge in axial direction. At, this second side facing away from the flow inlet edge the radially inner edge projects beyond the radially outer edge.

Abstract: A method is provided for coating a hollow, internally cooled blade (1) of a gas turbine, in which method an outer coating (5) comprising an MCrAlY-based bonding layer (6) and a ceramic thermal barrier layer (9) of zirconium oxide is applied to the base material (3) of the blade (1) on the outer side of the blade (1) and an inner coating (4) comprising a Cr diffusion layer (7) is applied to the base material (3) of the blade (1) on the inner side of the blade (1). The MCrAlY-based bonding layer (6) is thereby applied to the finished blade (1). At the same time, along with the inner coating (4), the Cr diffusion layer (7) is also applied to the MCrAlY-based bonding layer (6) of the outer coating (5) by chemical vapor deposition. Subsequently, an Al diffusion layer (8) and an outer brittle Al build-up layer are applied by chemical vapor deposition to the bonding layer (6) coated with the Cr diffusion layer (7).

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.

Abstract: An apparatus for at least intermittent metal-cutting machining of a support face of a bearing seat (5) of a concentrically guided shaft (3) with the bearing (4) dismantled is proposed, having at least one cutting tool (1) that is rotationally movable, in particular on a shaft (3) slidingly supported by bearing shells (4), such as a crankshaft of a large two-cycle diesel motor, in the gap created between the bearing seat (5) and a bearing journal (3) received in the bearing seat by dismantling of the bearing (4).

Abstract: An exhaust gas aftertreatment system for an internal combustion engine, particularly for a ship's diesel engine operated with heavy oil, has a SCR catalyst that uses ammonia as reductant. A nozzle is positioned upstream of the SCR catalyst viewed in flow direction of the exhaust gas. Using the nozzle, an aqueous urea solution is decomposed at a defined pressure and at a defined temperature to form water vapor, carbon dioxide and ammonia vapor such that ammonia evaporated by the nozzle is injected into the exhaust gas via the nozzle.

Abstract: A turbomachine has a first process control element, a second process control element, and a test system for testing the first process control element. The first process control element and the second process control element influence the same process variable. To test the first process control element, the test system changes the process variable by means of the second process control element. This change in the process variable caused by the second process control element is compensated again by means of the first process control element.

Abstract: A rotor of a turbomachine has a rotor base body and a plurality of rotor blades. Every rotor blade has a blade body and a coupling element segment. The coupling element segment of every rotor blade is contoured at a first side and at a second side opposite the first side that, at the first side and at the second side, a radially outer edge of the respective coupling element segment extends substantially in axial direction and a radially inner edge of the respective coupling element segment extends substantially in axial direction respectively delimit two surfaces separated from one another by a separating line. In at least one circumferential position of the rotor between two directly adjacent rotor blades, the separating lines run approximately parallel to, or in alignment with, the mounting direction of the rotor blades at the rotor base body, which mounting direction is defined by the blade roots.