Abstract: The proposed solution relates to a stator vane assembly for an engine, having at least one stator vane of a stator vane row and a casing for the at least one stator vane row, wherein the at least one stator vane is mounted adjustably on the casing by means of a bearing journal, which is rotatably mounted in a bearing opening in the casing and passes through this bearing opening along a longitudinal axis. A section of a sealing element, on which at least one sealing ridge extending radially in relation to the longitudinal axis is formed and/or which has a nonlinear slot passing longitudinally through the section, is provided within the bearing opening.

Abstract: The proposed solution relates to a stator vane assembly for an engine, having at least one stator vane of a stator vane row and a casing for the at least one stator vane row, wherein the at least one stator vane is mounted adjustably on the casing by means of a bearing journal, which is rotatably mounted in a bearing opening in the casing and passes through this bearing opening along a longitudinal axis. A section of a sealing element, on which at least one sealing ridge extending radially in relation to the longitudinal axis is formed and/or which has a nonlinear slot passing longitudinally through the section, is provided within the bearing opening.

Abstract: A rotor in BLISK or BLING design of an aircraft engine, comprising: a rotor disc that, at its radially outer area, forms an annulus which delimits the flow channel of the aircraft engine radially inside; and a plurality of rotor blades that project from the annulus; wherein the rotor disc forms a first structure and a second structure which are arranged at a distance from each other in the radial direction, wherein the first structure and the second structure respectively have an arm that protrudes upstream and/or downstream in the axial direction. An arm of the first structure arranged upstream and an arm of the second structure arranged upstream and/or an arm of the first structure arranged downstream and an arm of the second structure arranged downstream are connected to each other by means of a damping element that comprises an elastomer or is formed from an elastomer.

Abstract: A method for selecting a mistuning pattern of a turbomachine rotor disk includes providing information items relative to boundary conditions of a rotor disk excitation by forced vibrations; providing a reduced-order model of the rotor disk; producing a multiplicity of mistuning patterns of the rotor disk by entering the information items and the reduced-order model into a multi-objective optimizer and producing the mistuning patterns by the multi-objective optimizer while optimizing stability of the system in relation to self-excited vibrations while simultaneously optimizing stability of the system relative to forced vibrations. For each mistuning pattern produced, the reduced-order model is applied to a rotor disk, which implements the produced mistuning pattern, and the properties of this rotor disk are determined in view of self-excited vibrations and in view of forced vibrations. One of the mistuning patterns is selected for implementation.

Abstract: A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient.

Abstract: A rotor in BLISK or BLING design of an aircraft engine, comprising: a rotor disc that, at its radially outer area, forms an annulus which delimits the flow channel of the aircraft engine radially inside; and a plurality of rotor blades that project from the annulus; wherein the rotor disc forms a first structure and a second structure which are arranged at a distance from each other in the radial direction, wherein the first structure and the second structure respectively have an arm that protrudes upstream and/or downstream in the axial direction. An arm of the first structure arranged upstream and an arm of the second structure arranged upstream and/or an arm of the first structure arranged downstream and an arm of the second structure arranged downstream are connected to each other by means of a damping element that comprises an elastomer or is formed from an elastomer.

Abstract: A nose cone for a fan of an aircraft engine that comprises a cone part of fiber-reinforced material. It is provided that an elastomer is integrated into the cone part. The invention further relates to a fan and an aircraft engine with such a nose cone.

Abstract: A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.

Abstract: A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient.

Abstract: A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.

Abstract: In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life.

Abstract: In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life.