Abstract: The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

Abstract: A rotor (10) for a turbomachine, in particular for an aircraft engine, having a rotor base body (12), on which at least one sealing fin (14), which is disposed on a base (16), is provided for cooperating with an associated sealing element (20) of the turbomachine; relative to an axial direction of the rotor (10), the base (16) having a base portion (16a) disposed upstream of the sealing fin (14) and a base portion (16b) disposed downstream thereof, for supporting masks during the coating of sealing fins; the upstream base portion (16a) and the downstream base portion (16b) having different radial distances (A1, A2) to a radially outer sealing tip (18) of the sealing fin (14). Also, a turbomachine having at least one such rotor (10).

Abstract: A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity ? is at least 10% lower than the specific thermal conductivity ? of air.

Abstract: The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Abstract: The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.

Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Abstract: An inner ring according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface as well as a plurality of bearing mounts for a respective guide vane plate of a guide vane. The bearing mounts each have an opening in the outer inner ring surface as well as a bottom face lying radially opposite the opening. At least two of the bearing mounts are separated from each other by a separating wall and are connected to each other in a region of their bottom face by a through-opening. A guide vane cascade according to the invention for a turbomachine has an inner ring according to the invention and a plurality of guide vanes inserted into the bearing mounts.

Abstract: A rotor (10) for a turbomachine, in particular for an aircraft engine, having a rotor base body (12), on which at least one sealing fin (14), which is disposed on a base (16), is provided for cooperating with an associated sealing element (20) of the turbomachine; relative to an axial direction of the rotor (10), the base (16) having a base portion (16a) disposed upstream of the sealing fin (14) and a base portion (16b) disposed downstream thereof, for supporting masks during the coating of sealing fins; the upstream base portion (16a) and the downstream base portion (16b) having different radial distances (A1, A2) to a radially outer sealing tip (18) of the sealing fin (14). Also, a turbomachine having at least one such rotor (10).

Abstract: The invention relates to an inner ring system for an inlet guide vane cascade of a turbomachine. The inner ring system comprises an intermediate casing for accommodating structural loads and an inner ring, which is divided axially into a first ring segment and a second ring segment, which together form recesses for bearing radially inner end portions of guide vanes of the inlet guide vane cascade, wherein at least the second ring segment is fixed in place on the intermediate casing by screw connection. The invention further relates to an inner ring and to an intermediate casing for such an inner ring system, as well as a turbomachine that has such an inner ring system.

Abstract: A rotor stage (200) for a turbomachine, including a plurality of rotor blades (9), a rotor main body (7) having at least two rotor arms (3) and a balancing assembly (1) for balancing the rotor stage (200). The rotor arm (3) configured downstream from the rotor main body (7) features the balancing assembly (1). The balancing assembly (1) is configured between the axial end region of the rotor arm (3) and the rotor disk (27) of the rotor main body (7). Furthermore, a rotor drum (17, 18) for a turbomachine and a rotor (1000) for a turbomachine.

Abstract: The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, in particular a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.

Abstract: A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity ? is at least 10% lower than the specific thermal conductivity ? of air.

Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Abstract: A rotor stage (200) for a turbomachine, including a plurality of rotor blades (9), a rotor main body (7) having at least two rotor arms (3) and a balancing assembly (1) for balancing the rotor stage (200). The rotor arm (3) configured downstream from the rotor main body (7) features the balancing assembly (1). The balancing assembly (1) is configured between the axial end region of the rotor arm (3) and the rotor disk (27) of the rotor main body (7). Furthermore, a rotor drum (17, 18) for a turbomachine and a rotor (1000) for a turbomachine.

Abstract: The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Abstract: The invention relates to an inner ring system for an inlet guide vane cascade (14) of a turbomachine (10). The inner ring system comprises an intermediate casing (28) for accommodating structural loads and an inner ring (26), which is divided axially into a first ring segment (24a) and a second ring segment (24b), which together form recesses (22) for bearing radially inner end portions (18) of guide vanes (16) of the inlet guide vane cascade (14), wherein at least the second ring segment (24b) is fixed in place on the intermediate casing (28) by screw connection). The invention further relates to an inner ring (26) and to an intermediate casing (28) for such an inner ring system, as well as a turbomachine (10) that has such an inner ring system.

Abstract: An inventive guide vane ring casing 10? for a turbomachine has a casing surface 11 extending about and facing a central axis A, the casing surface having formed therein a plurality of receiving recesses 12?, each intended to receive a vane disk 21a of a guide vane 20. A radial cut-out 16 is formed between at least two adjacent receiving recesses 12? in the casing surface 11 and connects the two receiving recesses. A turbomachine includes a plurality of guide vanes 20 as well as an inventive guide vane ring casing 10?, each of the receiving recesses 12? in the guide vane ring casing having a guide vane disk 21a of a respective one of the guide vanes placed therein.

Abstract: An inner ring 10 according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface 11 as well as a plurality of bearing mounts 12 for a respective guide vane plate 21a of a guide vane 20. The bearing mounts 12 each have an opening 13 in the outer inner ring surface 11 as well as a bottom face 14 lying radially opposite the opening. At least two of the bearing mounts 12 are separated from each other by a separating wall 15 and are connected to each other in a region of their bottom face 14 by a through-opening 16. A guide vane cascade 100 according to the invention for a turbomachine has an inner ring 10 according to the invention and a plurality of guide vanes 20 inserted into the bearing mounts 12.

Abstract: Disclosed is a casing of a turbomachine which comprises at least a first casing portion comprising a first material having a first coefficient of thermal expansion and a second casing portion comprising a second material having a second coefficient of thermal expansion. The second casing portion comprises a casing structuring with flow-guiding elements and is connected in a force-fitting manner to the first casing portion by a radial press fit. Also disclosed are an installation safeguard and a turbomachine comprising the casing.

Abstract: Disclosed is a brush sealing arrangement for a turbomachine, comprising at least one stator, one rotor and one brush seal. The brush seal comprises at least one brush element and one ring for receiving the brush element. The brush sealing arrangement seals a gap between the stator and the rotor. The ring is connected to the stator by means of a press-fit. The ring comprises a first material having a first thermal expansion coefficient and at least a portion of the stator comprises for receiving the ring a second material having a second thermal expansion coefficient. Also disclosed are an installation securing arrangement comprising the brush sealing arrangement and a turbomachine.