Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.

Abstract: The present invention relates to a gas turbine having a housing (1), an outer sealing ring (2) that can be fastened detachably to the housing, a clamping member (3) for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove (10) and a radial flange (20) of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (sa) in the axial and/or peripheral direction.

Abstract: A method and an arrangement for monitoring an exhaust system of an internal combustion engine. Temperature profiles upstream and downstream of an installation location of a catalytic converter are measured in order to determine whether or not a catalytic converter is installed.

Abstract: The invention relates to an internal combustion machine (10), comprising a combustion engine (1) having an exhaust gas side (AGS) and a charging fluid side (LLS), and having a supercharger system (14) comprising an exhaust gas turbo charger (40) for charging the combustion engine (1), having a condenser array (41) on the charging fluid side (LLS) and a turbine arrangement (42) on the exhaust gas side (AGS), a compressor (3), the primary side (I) of which is connected to the charging fluid side (LLS), and the secondary side (II) of which is connected to the exhaust gas side (AGS). An electric machine (4) configured as a motor/generator is coupled to the combustion engine (1), wherein the electric machine (4) as a generator can be powered by the combustion engine (1), or can power the combustion engine (1) as a motor, wherein the compressor (3) can be powered directly by the electric machine (4) via a mechanical drive coupling (13).

Abstract: The invention relates to a suction housing (1) for an internal combustion engine, especially for arranging between a first (2) and a second (3) compressor of an internal combustion engine, characterized in that the suction housing (1) comprises an inner space (8) defined by a bottom element (9), a first (10) and a second (11) opposing lateral wall elements projecting from the bottom element (9), and a first (12) and a second (13) opposing front wall elements projecting from the bottom element. An open end (14) having an inlet (14a) via which charge air can enter the inner space (8) of the suction housing (1) is formed opposite the bottom element (9), and a web element (17) projecting from the bottom element (9) and arranged between the first (10) and the second (11) lateral wall elements is located in the inner chamber, said web element interconnecting the first (12) and the second (13) front wall elements.

Abstract: A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.

Abstract: A device for attaching seal elements in a recess, particularly in an installation groove designed in a flow machine, is disclosed. At least one fixing body is arranged between a seal carrier element and a clamping body assigned to the seal carrier element, where the fixing body is integrally connected to the seal carrier element and the clamping body by bar-like connections that can be detached when subjected to a force. In addition, at least one plastic deformable structure is designed on the fixing body. An attachment method as well as a production method for the device is also disclosed.

Abstract: A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component.

Abstract: A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.

Abstract: A method for heat-treating gas turbine blades, namely for locally heat-treating at least one gas turbine blade in a blade section thereof; a blade root section, which is not to be heat-treated, of the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the particular blade root section, which is not to be heat-treated, during the heat treatment of the particular blade section. The blade root section of the gas turbine blade is positioned in an interior space in a way that allows a remaining interior space of the holding receptacle, to be filled with a filler material; the holding receptacle, together with the gas turbine blade, being subsequently positioned in a heat treatment chamber to enable the gas turbine blade in the heat treatment chamber to undergo local heat treatment under vacuum.

Abstract: A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support (1) by a kinetic cold gas spraying process so as to form the structural component (11, 11?). A structural component which is made of a casting material and in which the structure is formed from a plurality of particles (17) that are interlinked and deformed using a cold gas spraying process.

Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).

Abstract: A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed.

Abstract: A method for machining an integrally bladed rotor of a fluid-flow machine is disclosed. In accordance with an embodiment of the invention, the method includes the steps of: a) providing an integrally bladed rotor having a main rotor body and several rotor blades integrally attached to the main rotor body; b) determining the natural frequency of each rotor blade of the integrally bladed rotor; and c) machining at least one rotor blade of the integrally bladed rotor by removing material to adjust the natural frequency of the particular rotor blade to a specified value.

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.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

Abstract: In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.

Abstract: A two-stage supercharger for an engine having a radial high-pressure turbine and an axial low-pressure turbine. The high-pressure turbine has a spiral housing with an exhaust-gas inlet connected to an exhaust line and via which exhaust-gas flows from the engine to the high-pressure turbine. A partial flow of the exhaust-gas flows past the high-pressure turbine in a bypass unit and is adjustable by a shut-off valve. The bypass unit includes a branch line and an annular duct housing integral with the spiral housing. The branch line branches off the exhaust-gas inlet at a point where the shut-off valve is arranged and issues into a duct of the annular duct housing. The partial flow flows through the branch line into the duct and an axially arranged annular gap into an exhaust-gas duct. The partial flow merges with a main exhaust-gas flow from the high-pressure turbine and flows into the low-pressure turbine.

Abstract: A method and device for producing a hole in an object is disclosed. The method includes the generation of a beam for removing material such that a bottom of a borehole is placed in a focus position of the beam, and a removal of material by impingement of the beam on the bottom of the borehole. A repeated placing of the bottom of the borehole in a focus position of the beam in order to compensate for the increased depth of the hole as a result of the removal of material is combined with a step of changing a radiation characteristic of the beam when the bottom of the borehole is repeatedly placed in a focus position.

Abstract: A system control unit for controlling a charging system that is intended for charging an electrical energy storage device, comprising an electric generator; an internal combustion engine that is mechanically connected with the electric generator; a generator controller for controlling the electric generator; an engine controller for controlling the internal combustion engine; and a transmitting device for transmission of messages, whereby the engine controller is connected with the generator controller by way of the transmitting device, and whereby the engine controller is operable in that a message containing information about an operating state of the internal combustion engine can be produced and said message can be sent to the generator controller via the transmitting device.