Abstract: A containment for a continuous flow machine, in particular for a gas turbine, is disclosed. The containment has at least one annular housing with at least one axial section of lesser radial wall thickness and at least one axial section adjacent thereto of greater wall thickness, where the housing is designed and constructed so that the section of greater wall thickness is at a distance in the axial direction of the continuous flow machine from a trailing edge of a guide vane lying downstream in the direction of flow of the continuous flow machine, and extends downstream in the direction of flow of the continuous flow machine over a leading edge of the next downstream guide vane.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: Exemplary illustrations are provided of a common rail system for an internal combustion engine, having a rail for fuel and an injector for the purpose of injecting the fuel into a working space of the internal combustion engine, said injector having a fluid connection to said rail via a high-pressure conduit. The high-pressure conduit may have a high-pressure component with an individual reservoir, and the high-pressure conduit and/or the rail may have a pressure measurement device. The pressure measurement device may be coupled to a local logic and storage device of a decentralized, local electronic device which is designed for the purpose of locally analyzing and storing measurement data of the pressure measurement device, e.g., injector data and/or rail data, and the pressure measurement device is connected to the central electronic device via a bus, with the local logic and storage device connected between the same.

Abstract: A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

Abstract: A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge.

Abstract: The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.

Abstract: A method for torque control of an internal combustion engine includes a pressure sensor that is associated with at least one, but at the most two cylinders of the internal combustion engine, whereby an cylinder internal pressure for the cylinder associated with the pressure sensor is detected. The method carries out an adjustment of injection characteristics for the injectors allocated to the individual cylinders of the internal combustion engine by way of a method which is independent from the detected cylinder pressure. A torque control for the internal combustion engine is performed based on the detected cylinder pressure.

Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.

Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).

Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.

Abstract: Disclosed are a turbomachine having at least one radial gap seal which has at least two opposite ceramic coatings which are constructed in each case from a ceramic powder, the particle size of which is smaller than 1.0 ?m, and a turbomachine having at least one radial gap seal, wherein the coatings are built up from powder-based individual layers, the outer layer of which has a higher ceramic fraction than a base layer close to the rotor or stator section respectively, wherein the particle size of the powder material is smaller than 1.0 ?m.

Abstract: A method for machining a robot-guided component with a tool which is fastened in an articulated manner to a tool holder is disclosed. The method includes detecting a deflection of the tool with respect to the tool holder from a desired position and changing a pose of a robot that is guiding the robot-guided component on a basis of the detected deflection.

Abstract: A method for determining the aging of an oxidation catalyst in an exhaust gas aftertreatment system of an internal combustion engine, having the following steps: ascertaining a soot burn rate of a particle filter of the exhaust gas aftertreatment system; adapting a function having at least one adaptation parameter to the soot burn rate dependent on at least one variable, a value of the adaptation parameter depending on an aging of the oxidation catalyst; and determining the aging of the oxidation catalyst using the adaptation parameter value ascertained by adapting the function.

Abstract: A method for regenerating a particle filter during the operation of an internal combustion engine, having the following steps: detecting at least one loading parameter which is characteristic of a present loading of the particle filter, wherein an active regeneration measure can be carried out recurrently in a manner dependent on the loading parameter; determining a time window for a regeneration of the particle filter; and determining a prediction for an operating state of the internal combustion engine expected within the time window, wherein the active regeneration measure at a time indicated for it by the loading parameter is skipped if the prediction predicts that, within the time window, an operating state of the internal combustion engine will arise in which a regeneration of the particle filter takes place without an active regeneration measure.

Abstract: An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face.

Abstract: Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a ??-phase are present in a ?-matrix with a fraction of 40 to 50 vol % at 1050° C. to 1100° C., and a ?/?? mismatch at 1050° C. to 1100° C. is from ?0.15% to ?0.25%. The alloy comprises 11 to 13 at % aluminum, 4 to 14 at % cobalt, 6 to 12 at % chromium, 0.1 to 2 at % molybdenum, 0.1 to 3.5 at % tantalum, 0.1 to 3.5 at % titanium, 0.1 to 3 at % tungsten. The tungsten content of the ?-matrix is greater than that in the precipitated ??-phases.

Abstract: The invention relates to a method and an arrangement for operating an internal combustion engine. In the method a first distribution of values for at least one variable is used, the variable describing a physical property of the internal combustion engine, and over a second time period values for this variable are recorded and classified, such that a second distribution is determined. The first distribution is then compared with the second distribution such that the behavior of the internal combustion engine can be adapted on the basis thereof.

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: Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases.

Abstract: Reciprocating-piston internal combustion engines having different power outputs are to be equipped simply, reliably and inexpensively with a device for the selective catalytic reduction of the exhaust gases having an SCR module for a reciprocating-piston internal combustion engine, comprising a housing and/or a frame, an exhaust-gas section which delimits a flow duct for guiding through exhaust gas, having an inlet opening for introducing the exhaust gas and an outlet opening for discharging the exhaust gas, an SCR catalytic converter which is arranged inside the flow duct, at least one injection element for adding a reducing agent, for example ammonia or a urea solution, to the exhaust gas which is guided through the flow duct. This problem is solved by virtue of the fact that the SCR module comprises at least one delivery device (13) for feeding the reducing agent to the injection element at a predetermined pressure.