Abstract: The present invention relates to a module for a turbomachine, with a guide vane arrangement, a seal carrier, which is arranged radially inside an inner platform of the guide vane arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding member as well as a connecting element, wherein the first seal carrier wall and the seal carrier are formed in a one-piece manner with each other, and wherein the seal carrier walls are multipiece in construction relative to each other, and the second seal carrier wall is fastened to the first seal carrier wall and the seal carrier by way of the connecting element, wherein the sliding member holds the seal carrier walls spaced apart from each other in such a manner that they bound axially an intervening space with each other.

Abstract: The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.

Abstract: The present invention relates to a module for a turbomachine, with a guide vane arrangement, a seal carrier, which is arranged radially inside an inner platform of the guide vane arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding member as well as a connecting element, wherein the first seal carrier wall and the seal carrier are formed in a one-piece manner with each other, and wherein the seal carrier walls are multipiece in construction relative to each other, and the second seal carrier wall is fastened to the first seal carrier wall and the seal carrier by way of the connecting element, wherein the sliding member holds the seal carrier walls spaced apart from each other in such a manner that they bound axially an intervening space with each other.

Abstract: A damper ring (1) for reducing unwanted vibrations of a blisk (2), which damper ring (1) is disposable at the radially inner side of a blade ring (3) of the blisk (2). The damper ring (1) features at least one damper element (4) configured to dissipate vibrational energy of the blisk (2) and/or to transfer vibrational modes of the blisk into vibrational modes different from the vibrational modes of the blisk. The invention also relates to a blisk (2) and to a turbomachine (13).

Abstract: A module for a turbomachine, including a guide blade arrangement, a seal carrier that is situated radially within an inner platform of the guide blade arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding body as well as a connecting element. The seal carrier walls have a multipart design with respect to one another, and the second seal carrier wall is fastened to the first seal carrier wall and to the seal carrier via the connecting element. The sliding body holds the seal carrier walls at a distance from one another in such a way that they mutually axially delimit a clearance in which the guide blade arrangement engages via a radially inwardly extending guide pin. A radially inner section of the second seal carrier wall has frictional contact relative to the seal carrier.

Abstract: An arrangement reduces oscillation of an oscillatory structure. The arrangement has: a structure having at least one mode in at least one direction; and an oscillation-reducing device. The oscillation-reducing device includes a housing on the structure; a cavity; and a body. The body is configured to make impact contact with a first surface portion and a second surface portion of an inner wall of the housing and disposed is in the cavity such that the body can make impact contact with the first surface portion and the second surface portion of the inner wall of the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least one direction. The first surface portion or the second surface portion of the inner wall of the housing has a curved profile.

Abstract: An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (40; 40?) is fastened by at least one fastening element (30; 30?) which engages for this purpose into an opening (41) of the impulse element housing and into an opening (11) of the rotor, the impulse element housing having at least one cavity (44) in which at least one impulse element (5) is accommodated with play.

Abstract: An arrangement reduces oscillation of an oscillatory structure. The arrangement has: a structure having at least one mode in at least one direction; and an oscillation-reducing device. The oscillation-reducing device includes a housing on the structure; a cavity; and a body. The body is configured to make impact contact with a first surface portion and a second surface portion of an inner wall of the housing and disposed is in the cavity such that the body can make impact contact with the first surface portion and the second surface portion of the inner wall of the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least one direction. The first surface portion or the second surface portion of the inner wall of the housing has a curved profile.

Abstract: A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

Abstract: An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (40; 40?) is fastened by at least one fastening element (30; 30?) which engages for this purpose into an opening (41) of the impulse element housing and into an opening (11) of the rotor, the impulse element housing having at least one cavity (44) in which at least one impulse element (5) is accommodated with play.

Abstract: A guide vane segment for a gas turbine having at least one guide vane, a radially inner covering strip and a radially outer covering strip, wherein the at least one guide vane extends between the inner covering strip and the outer covering strip. The inner covering strip and/or the outer covering strip having a respective support portion which extends in a circumferential direction (UR) and has a respective axial end face. The support portion comprises on the respective inner covering strip and/or the respective outer covering strip at least one support portion rib which extends in a radial direction, is connected to the support portion, and comprises a rib end face which merges into the axial end face of the support portion.

Abstract: A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

Abstract: The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (?) that is different from a zero angle.

Abstract: The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.

Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.

Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

Abstract: An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.

Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.