Abstract: An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, the vane comprising a radially outer bearing section, a radially inner bearing section, and a vane section, which extends in the radial direction between the outer bearing section and the inner bearing section, wherein the outer and the inner bearing sections are designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner bearing section is configured like a journal (cone-shaped) and has a lateral surface that is formed circumferentially about the vane axis, the lateral surface being of convex shape. In this way, it is provided that the radius of curvature of the convex lateral surface is at least double the maximum diameter of the bearing section.

Abstract: An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, said vane comprising a radially outer storage section, a radially inner storage section, and a vane section, which extends in the radial direction between the outer storage section and the inner storage section, wherein the outer and the inner storage sections are designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner storage section is designed like a journal (cone-shaped) and has a casing surface that revolves relative to the vane axis, said surface being of convex shape. In this way, it is provided that the radius of curvature of the convex casing surface is at least double the maximum diameter of the storage section.

Abstract: A vane assembly for a turbomachine includes a variable vane (10-15), the vane having at least one first, in particular plane or curved, engagement surface (11; 11?) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.

Abstract: The present invention relates to a guide vane ring element for a turbomachine, such as a gas turbine, with at least one drilled hole for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion and, in particular, has a radius.

Abstract: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.

Abstract: A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.

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: 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: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.

Abstract: A vane assembly including a variable vane (10-15) for a turbomachine is provided, the vane having at least one first, in particular plane or curved, engagement surface (11; 11?) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.

Abstract: A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

Abstract: A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.

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 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: 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: 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: The present invention relates to a guide vane ring element (10) for a turbomachine, such as a gas turbine, with at least one drilled hole (30) for the at least partial uptake of a flange (21) of a rotatable guide vane (20), wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion (31A, 31B) and, in particular, has a radius (R).

Abstract: A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.