Abstract: Gas engine arrangement having a gas engine, a gas rail, via which a first gas in the form of fuel gas can be supplied to at least one gas metering device of the gas engine, and a gas control section, which is designed to supply fuel gas to the gas rail via a supply path on the outflow side. A purge line is passed into the gas rail. The gas engine arrangement is designed to selectively supply fuel gas or a second gas to the purge line, and the gas engine arrangement is designed to displace gas from the gas rail and to discharge it via the supply path when the fuel gas or second gas is supplied to the purge line.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a turbine section that has a fan drive turbine rotor, and a compressor rotor. A gear reduction effects a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of blade rows of the compressor rotor, and the blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in at least one of the blade rows and the rotational speed are such that the following formula holds true for the at least one of the plurality of blade rows of the compressor rotor: (the number of blades×the rotational speed)/60 sec?about 5500 Hz. A method of designing a gas turbine engine is also disclosed.

Abstract: A gas mixer for mixing a first gas and a second gas, having a first, outer gas housing part, having an inlet for the first gas in a longitudinal axis and an inlet for the second gas in a transverse axis, a second, interior gas housing part set into the first gas housing part to form an annular space for a second gas, having a mixing space into which the first gas and the second gas are introduced for mixing. The first and second gas housing parts and the annular space are aligned along the longitudinal axis and the mixing space is aligned cylindrically along the longitudinal axis. A mixing device having a plurality of hollow rods is arranged in the mixing space. A hollow space of a hollow rod is in fluid communication on both sides with the annular space. The number of hollow rods extends transverse to the longitudinal axis and the transverse axis and at least one hollow rod has a plurality of openings for the second gas, so that the hollow space is in fluid communication with the cylindrical mixing space.

Abstract: The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material. The invention also relates to an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine, and to an aero engine having a housing (10), in which at least one insulation element (12) is arranged radially above at least one guide vane (14).

Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.

Abstract: In a multi-fuel injector for an internal combustion engine, including a housing with a nozzle needle movably disposed therein between a closed position in which the nozzle needle blocks a discharge of fuel from a collection chamber, to which a first fuel is supplied, above the nozzle needle, a control chamber is arranged to which a high pressure second fuel is supplied which acts on the nozzle needle to bias it into a closed position, and a control valve is provided in a pressure release line extending from the control chamber for a controlled release of the second fuel from the control chamber by opening the control valve so as to relief the closing pressure on the nozzle needle in order to permit lifting of the nozzle needle from the closed position for discharging the fuel from the collection chamber.

Abstract: A method for controlling an internal combustion engine, wherein a first engine control device generates a control signal to actuate a function of the engine. A switchover device transmits the control signal of the first control device to the engine to actuate the function of the engine. The first control device transmits a sign-of-life signal which indicates functionality of the control device to the switchover device. The first engine control device does not transmit the sign-of-life signal or transmits the signal incorrectly if a fault occurs which endangers proper actuation of the function of the engine by the first engine control device. If the sign-of-life signal of the first engine control device is not or is incorrectly received by the switchover device, the switchover device stops transmitting the control signals of the first engine control device and starts transmitting a control signal generated by a second engine control device to the engine to actuate the function of the engine.

Abstract: A cooling system including a first coolant line and a second coolant line, at least one first component to be cooled, into which the first coolant line opens, and a first ventilation line. The first ventilation line is fluidically connected to the at least one first component and is configured for ventilating the at least one first component. The first ventilation line opens into the second coolant line.

Abstract: A blading for a turbine, in particular a gas turbine, is disclosed. The blades of the blading in a section near the tip have a distribution ratio (t/l) of at least 0.70, in particular at least 0.9, and/or at most 0.97, in particular at most 0.95. A downstream flow angle (?) is at most 167°, in particular at most 165°, and at least 155°, in particular at least 160°. In addition, or alternatively, an acceleration ratio (w2/w1) is at least 1.4, in particular at least 1.5.

Abstract: A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.

Abstract: A method for determining residual stresses of a component (14), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool (26) in a surface (24) of the component (14) to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool (26); and determining the residual stresses of the component (14) which are present at least in the region around the created melt pool (26) based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component (14) while it is being manufactured by an additive manufacturing process is provided.

Abstract: A method for coating a component of a turbomachine is disclosed. The method includes covering a first surface of the component with a covering device, where the covering device is profiled in a zigzag shape. The method further includes applying a coating material via cold kinetic compaction or kinetic cold gas spraying on the component such that a second surface of the component is coated with the coating material and such that particles of the coating material are deflected off of the covering device so that the particles do not adhere to the covering device.

Abstract: The invention relates to a method for detecting the failure of injectors in an internal combustion engine, comprising the following steps: measuring a crank angle signal; transforming the crank angle signal into the frequency range by means of a discrete Fourier transformation; switching off each injector once and in a sequential manner; detecting and storing an angle of the harmonic of the 0.5th order of the Fourier-transformed crank angle signal for each switched-off injector once and in a sequential manner; continuous detection and storage of an angle and an amount of the harmonic of the 0.

Abstract: Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing.

Abstract: The invention relates to a device (10) and method for the generative production of a component (12). The device comprises two supply tanks (14a, 14b) for taking up powder-form material (16), two overflow tanks (22a, 22b) for taking up excess powder-form material (16), wherein a closing means (24a, 24b) is assigned to each overflow tank (22a, 22b), this means being switchable between a closed position, in which powder-form material (16) cannot be transported into the respective overflow tank (22a, 22b), and an open position, in which powder-form material (16) can be transported into the respective overflow tank (22a, 22b).

Abstract: The invention relates to a method for electrochemically machining blades of a turbomachine having at least one U-shaped or trapezoidal cross-sectional profile of the surface to be treated, wherein an electrode array having at least three electrodes that can be moved in different directions is provided. The electrodes are moved from a start position having a first distance to the surface to be machined into an end position having a second distance to the surface to be machined, wherein in the end position, a closed work surface of the electrodes having a negative shape of the surface contour of the surface to be machined is located opposite thereof. The invention further relates to an electrode array for carrying out an electrochemical machining, wherein the electrode array comprises at least three electrodes that can be moved in different directions to one another, and to stationary mounting, wherein the electrodes can be moved from a start position to an end position.

Abstract: A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system.

Abstract: In a tank cleaning arrangement for cleaning liquid fuel stored in a fuel tank, the fuel is circulated from various selectable outlet areas to various selectable inlet areas provided on the tank via a conduit system including circulating pumps and filters arranged at various locations. At least one circulating pump is driven mechanically by an engine associated with the tank cleaning arrangement, whereby the tank cleaning arrangement is shut down automatically when the engine is shut down, so that a control as well as a separate drive system for the at least one circulating pump can be omitted. Also a combustion engine with such tank cleaning system is and an operating method for the tank cleaning arrangement are 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 blade of a turbomachine is disclosed. A contour variation is provided on the suction side of the blade, where the contour variation has a negative step as viewed in a direction of flow. The step has a stepped surface extending perpendicularly to a contour of the suction side and the contour variation has a tangential surface which leads upstream tangentially on the contour of the suction side starting from a step edge.