EP3536913B1 - Inner ring for a turbomachine and method for producing said inner ring - Google Patents

Inner ring for a turbomachine and method for producing said inner ring Download PDF

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Publication number
EP3536913B1
EP3536913B1 EP19160760.5A EP19160760A EP3536913B1 EP 3536913 B1 EP3536913 B1 EP 3536913B1 EP 19160760 A EP19160760 A EP 19160760A EP 3536913 B1 EP3536913 B1 EP 3536913B1
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EP
European Patent Office
Prior art keywords
inner ring
recess
turbomachine
guide vane
peripheral contour
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19160760.5A
Other languages
German (de)
French (fr)
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EP3536913A1 (en
Inventor
Lothar Albers
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3536913A1 publication Critical patent/EP3536913A1/en
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Publication of EP3536913B1 publication Critical patent/EP3536913B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional

Definitions

  • the present invention relates to an inner ring for a vane ring for attachment to, in particular adjustable, vanes of a turbomachine, in particular a compressor or turbine stage of a gas turbine, a vane ring and a turbomachine, in particular a gas turbine, with such an inner ring and a method for its production.
  • the inner rings are generally exposed to thermal loads, in particular partially changing and/or high temperature gradients, in particular due to the working fluid flowing through the guide vane ring and thus at least partially flowing around the inner ring and/or due to rubbing seals between the guide vane ring and a rotor rotating relative to this.
  • thermal loads in particular partially changing and/or high temperature gradients
  • undesirable, thermally induced deformations of the inner ring can occur, in particular the widening of gaps and, as a result, undesirable leaks, which can have a disadvantageous effect on the efficiency of the turbomachine.
  • Generic inner rings are known in principle from the prior art, for example from FR 2 953 487 , where the FR 2 953 487 teaches the use of a polygonal inner ring which, relative to the inner ring in a functional installed state in a turbomachine, has reinforcing elements, in particular reinforcing ribs, extending in the radial direction outwards and in the circumferential direction between the receptacles for the guide vanes. More inner rings are from the EP 3 032 037 A1 , EP 31 76385 , DE 695 05 074 T2 and U.S. 2015/275916 A1 known.
  • an inner ring which has isolated slot-shaped recesses between the receptacles of the guide vanes.
  • the cutouts serve to influence the cording effect in a targeted manner, in which the hoop stresses and the radial temperature gradient is affected.
  • the disadvantage is that the recesses are slot-shaped and are not adapted to the contour of the recesses for the guide vanes, which for the purpose of the invention disadvantageously interrupts the circumferential stress profile and can lead to stress peaks in the base of the slots.
  • An object of an embodiment of the present invention is to provide an improved inner ring.
  • an inner ring for a guide vane ring for attachment to, in particular adjustable, guide vanes of a turbomachine, in particular a compressor or turbine stage of a gas turbine has a plurality of guide vane receptacles arranged spaced apart from one another in the circumferential direction, in particular recesses, each of which is intended to accommodate a Fastening element, in particular a fastening pin, a vane are formed.
  • the inner ring has at least one indentation with a wall thickness that is reduced in the radial direction compared to an area outside of the indentation that adjoins the indentation.
  • the indentation in particular the at least one indentation, has a greater extent in the axial direction than in the circumferential direction in relation to an axis of rotation of a turbomachine when the inner ring is functionally installed in a turbomachine.
  • the directional statement “axial” refers in a manner customary in the art to a direction parallel to the axis of rotation or (main) machine axis of the turbomachine, the directional statement “circumferential direction” correspondingly to a direction of rotation around this axis of rotation or (main) machine axis, the directional statement “ radial” to a direction perpendicular to the axial and circumferential directions.
  • the directional statement “tangential” accordingly refers to a direction which is perpendicular to the axial direction and the radial direction, with all directional statements relating in particular to an inner ring according to the invention and/or a vane ring according to the invention being related to a functional installation state in a turbomachine.
  • Guide vane receptacles in the sense of the present invention are in particular recesses or recesses, in particular blind hole-like or continuous recesses or recesses in which guide vanes can be radially supported and/or rotatably mounted.
  • a “depression” within the meaning of the present invention is understood here to mean in particular a local indentation or depression or the like in the radial direction.
  • an improved temperature distribution in particular a more advantageous temperature profile in the radial direction, can be achieved by one or more such depressions in the inner ring.
  • the indentation(s) can influence, in particular reduce, a thermally induced movement and/or deformation of the inner ring during operation, and thus in particular a change in its shape, in particular its diameter and/or its roundness, can be influenced, in particular reduced.
  • a sealing effect between the guide vanes and the inner ring in the area of the guide vane mounts and/or between the guide vane ring and the rotor and/or an inlet can be reduced and the operating behavior of a turbomachine, in particular its efficiency, can be improved.
  • one or more such indentations can in particular reduce what is known as the undesired "cording effect".
  • the "cording effect” is understood to mean a three-dimensional, thermally induced deformation of the inner ring, in particular a thermally induced formation of constrictions in the inner ring, which can occur at the dividing planes in particular in the case of divided inner rings and which are caused in particular by a transient, radial Temperature profile as a result of the different heating times of the inner ring on the side of the guide vanes, which is heated directly by the working fluid and thus quickly, and the side facing away from the guide vanes, which heats up slowly.
  • the different heating times of the inner ring on the side of the guide vanes and the side facing away from the guide vanes can lead to different, thermally induced expansions of the material, in particular to a greater expansion of the material on the side facing the guide vanes than on the side facing away from the guide vanes Side and thus to a thermally induced deformation of the inner ring, similar to a bimetal.
  • gaps can in particular widen and, as a result, undesired leaks can occur, which can have a disadvantageous effect on the efficiency of the turbomachine.
  • the indentation(s) according to the invention locally reduces the cross-sectional area of the inner ring, in particular a wall thickness of the inner ring, in particular in the radial and/or axial direction and/or in the circumferential direction, depending on the design of the indentation.
  • an improved, transient heating behavior of the inner ring can advantageously be achieved, since less material of the inner ring has to be heated.
  • an improved, transient temperature profile can be achieved in the radial direction, in particular a temperature profile with a lower temperature gradient in the radial direction, which, in particular with a suitable design of the recess(es), in relation to the "cording effect " improved heating behavior of the inner ring, in particular one that reduces the "cording effect”.
  • an undesired widening of gaps in particular an ovalization of the guide vane mounts, and/or sealing fins running into the one sealing structure of a seal carrier, can be reduced or even completely avoided, which reduces leakage and, as a result, the efficiency the turbomachine can be improved and/or a specific fuel consumption reduced and/or in the case of a turbomachine designed as a compressor a surge limit can be increased.
  • a “surge limit” is understood to mean a stable volumetric flow that is at least required to achieve a desired compression ratio, with a higher compression being generally possible with an increasing volumetric flow.
  • a higher, more stable volume flow can be achieved due to a lower leakage. This in turn allows a higher compression ratio to be achieved, so that a reduction in leakage can result in a higher compression ratio.
  • the wall thickness of the inner ring which is locally reduced as a result of the depression(s) according to the invention, also reduces the flexural rigidity of the inner ring, in particular in the circumferential direction, which, in one embodiment of the invention, results in one, in particular further, improvement in the "cording properties", in particular a (further) reduction of the "cording effect" can be achieved.
  • a vane ring with a more flexible inner ring and a more rigid seal carrier can be provided in this way, with which the "cording effect" can be reduced particularly well, as has been found.
  • the weight of the inner ring and thus of a ring of guide vanes and a turbomachine can be reduced by the indentation(s) according to the invention.
  • the present invention has at least one depression with an hourglass-shaped or hourglass-like peripheral contour, in particular based on a projection of the peripheral contour of the depression into a tangential plane of the inner ring. It has been found that a particularly advantageous thermal behavior of the inner ring can be achieved in this way, in particular a particularly advantageous thermal movement and/or deformation of the inner ring, in particular a thermally induced movement/deformation of the inner ring, which leads to a particularly small deviation from roundness , In particular, leads to a particularly low degree of ovalization of the inner ring and/or the vane mounts.
  • the inner ring is designed in particular in such a way, in particular the indentations of the inner ring, that the inner ring has a bending stiffness that is reduced by at least 10%, in particular by at least or around 15%, in particular in the circumferential direction, compared to an inner ring without indentations.
  • the inner ring has in particular a plurality of indentations, in particular a plurality of indentations each arranged on a side of the inner ring facing away from the guide vanes, the indentations being distributed, in particular at least substantially equidistantly, over the circumference of the inner ring.
  • a particularly advantageous heating behavior and/or an advantageous reduction in the flexural rigidity of the inner ring can be achieved.
  • exactly one depression is provided at least between two adjacent guide vane mounts or adjacent groups of guide vane mounts, in particular in each case.
  • the inner ring has exactly one indentation, in particular between at least one pair of adjacent pairs of guide vane mounts or a pair of adjacent groups of guide vane mounts, in particular between two guide vane mounts or two groups of guide vane mounts exactly one indentation.
  • a particularly advantageous heating behavior and/or an advantageous reduction in the flexural rigidity of the inner ring can be achieved, in particular an advantageous, in particular more uniform, heating behavior over the entire circumference of the inner ring or a (more) uniform flexural rigidity of the inner ring circumferential direction.
  • At least one indentation based on a functional installation state of the inner ring in a turbomachine, is arranged on a side of the inner ring facing away from the guide vanes, in particular in a surface of the inner ring lying on the inside in the radial direction, in particular in an inner lateral surface of the inner ring.
  • the inner ring can also be introduced into at least one surface of the inner ring facing the guide vanes.
  • the peripheral contour of at least one depression runs in particular at least partially parallel to a peripheral contour of an adjacent recess, in particular in an area of the peripheral contour that extends essentially in the axial direction of the inner ring, based on a functional installation state in a turbomachine, wherein the peripheral contour runs in particular at least partially parallel to the peripheral contours of both adjacent recesses.
  • the peripheral contour of at least one depression runs in particular at least partially parallel to a contour of the inner ring in the peripheral direction of the inner ring, in particular in a region of the peripheral contour that extends essentially in the peripheral direction of the inner ring, based on a functional installation state in a turbomachine.
  • the peripheral contour is in particular embodied symmetrically or asymmetrically in and/or with respect to an axial direction.
  • a “tangential plane” is understood to mean a plane that is perpendicular to the radial direction, in particular a plane that extends perpendicular to an associated radius.
  • At least one depression has a peripheral contour that is completely closed or open at at least one axial end, in particular only at one axial end.
  • a depression with a peripheral contour that is open at its axial ends can be produced particularly easily, in particular by machining.
  • a depression with a completely closed peripheral contour generally leads to less leakage than a comparable depression with a peripheral contour that is open at one axial end, since, in particular, the peripheral contour closed at the axial ends reduces or prevents the working fluid from flowing from the guide vane side through the open end into the depression on the side of the inner ring facing away from the guide vanes.
  • At least one indentation has a bottom surface, with the indentation having a constant depth, in particular at least in the area of the bottom surface, at least partially, in particular over the entire bottom surface, in particular such that the inner ring in the area of the bottom surface has in particular a has a constant wall thickness and/or an inner contour with a constant radius in relation to the (main) machine axis or the axis of rotation of the turbomachine in relation to a functional installation state of the inner ring in a turbomachine.
  • an effective wall thickness reduction can be achieved in a particularly simple manner, in particular with simultaneous advantageous thermal behavior of the inner ring.
  • the depth of at least one indentation is selected to be as large as possible and as a result the wall thickness is minimized, particularly locally in the area of the indentation and/or in an area adjoining the indentation.
  • the inner ring is designed in one piece. In another embodiment of the present invention, the inner ring is designed in multiple parts, in particular divided in the circumferential direction and/or in the axial direction.
  • the inner ring is divided in the circumferential direction, it has in particular several inner ring segments and is in particular composed of several inner ring segments, in particular of at least two inner ring segments, which in this case preferably each extend over a circumferential angle of approximately, in particular exactly, 180 ° extend or from three inner ring segments, which preferably each extend over a circumferential angle of about, in particular exactly, 120 °.
  • two inner ring segments adjoining one another in the circumferential direction are coupled, in particular connected, to one another at their abutting surfaces, in particular with the aid of at least one connecting pin or connecting pin extending in the circumferential direction.
  • the inner ring or at least one inner ring segment can be divided in the axial direction, with the division extending in particular over the entire length of the inner ring or the inner ring segment in the circumferential direction and in particular in a common radial plane through the inner ring or The associated inner ring segment runs.
  • the individual inner ring parts are coupled, in particular connected, to one another with the aid of at least one connecting pin or pin extending in the axial direction.
  • At least one indentation in particular all indentations, has been made in the inner ring by a separating manufacturing process, in particular by mechanical processing, in particular by machining, in particular by machining with a geometrically defined cutting edge, in particular by milling.
  • the depressions can be introduced into the inner ring in a particularly simple manner.
  • particularly simple and precise indentations can be introduced in this way.
  • a ring of guide vanes according to the invention for a turbomachine in particular a compressor or turbine stage of a gas turbine with an inner ring and, in particular, adjustable guide vanes to which the inner ring is attached, has an inner ring designed according to the present invention as described above.
  • At least one guide vane is connected to the inner ring by means of a fastening pin that extends in the radial direction and is inserted into a correspondingly designed guide vane receptacle of the inner ring, in particular supported on the inner ring in the radial direction, in particular rotatable about a longitudinal axis in the inner ring stored.
  • a receiving bushing is also provided between the inner ring and the mounting pin.
  • the vane ring has in particular an additional seal carrier or a seal carrier segment, the seal carrier or the seal carrier segment being arranged in particular on the side facing away from the guide vanes and in particular at least one depression arranged in a surface remote from the guide vanes, at least partially, in particular completely covers.
  • a turbomachine according to the invention in particular a gas turbine, with at least one compressor or turbine stage with an inner ring has an inner ring designed according to the present invention as described above.
  • a turbomachine has, in particular, one or more compressor and/or turbine stages.
  • one or more of these compressor and/or turbine stages each have a rotor cascade and a guide cascade, with one or more of these guide cascades in particular having a guide vane ring according to the invention.
  • the invention is used in gas turbines, in particular in gas turbine engines, in particular in a high-pressure and/or low-pressure compressor.
  • the turbomachine is therefore in particular a compressor, in particular a high-pressure or low-pressure compressor.
  • An inner ring according to the invention is produced in one embodiment of a method according to the present invention in that at least one indentation of the inner ring, in particular all indentations, is produced by a separating manufacturing process, in particular by mechanical processing, in particular by machining, in particular by machining with a geometrically defined cutting edge , especially by milling.
  • FIG. 1 shows a section of a generic vane ring segment 1 known from the prior art of a turbomachine designed as a compressor known from the prior art with an inner ring segment 20 in the region of the inner ring segment 20 in a side view for a better understanding of the invention.
  • the inner ring segment 20 is fastened to the guide vanes 10 in a manner known from the prior art, with the inner ring segment 20 having guide vane receptacles 24 distributed uniformly in the circumferential direction, in particular designed as through-openings, the guide vanes 10 having fastening pins extending in the radial direction y 11 are connected to the inner ring segment 20 and are supported on the inner ring segment 20 in the radial direction.
  • the guide vanes 10 are designed to be adjustable and are connected to the inner ring segment 20 so as to be rotatable about a longitudinal axis L.
  • a bushing 25 is introduced into the passage opening for the guide vane mount 24 .
  • the guide vane ring 1 For sealing against the rotatably mounted rotor 30 of the turbomachine, the guide vane ring 1 also has a seal carrier segment 21 fastened to the inner ring segment 20 on a side facing away from the guide vanes 10, with the seal carrier segment 21 also being arranged in a known manner on the inner ring segment 20, with in this case , in particular for the benefit of a high sealing effect, the guide vane receptacles 24 embodied as through openings are covered by the seal carrier segment 21 on a side of the inner ring facing away from the guide vanes 10 .
  • a sealing structure 22, in particular a honeycomb-shaped sealing structure 22, is provided on a radial inner side of the seal carrier segment 21, which interacts with so-called sealing fins 31, which are fastened to the rotor and extend outwards in the radial direction from the rotor, and which creates a gap between the guide vane ring or guide vane ring segment 1 fixedly arranged on the housing and the rotatably mounted rotor 30 of the turbomachine in order to reduce flow losses due to leaks when flowing around the guide vanes 10, in particular a reduction in the volume flow in the area of the guide vanes 10.
  • the vane ring segment 1 is part of a vane ring, which is divided in the circumferential direction into several vane ring segments 1, each Guide vane ring segment 1 has an inner ring segment 20 and a corresponding seal carrier segment 21 .
  • each inner ring segment 20 has a connecting pin 23 on one of its end faces in the circumferential direction and a connecting pin 23 on the other end face, which is not shown here and is designed to correspond to the connecting pin 23 recess.
  • FIG. 2 shows a section of the vane ring segment 1 in a perspective representation, in this representation the connecting pin 23 on the end face of the inner ring segment 20, the guide vane receptacles 24 designed as through-openings and the bushings 25 arranged in the through-openings for the guide vane receptacles 24 can be seen particularly well.
  • a working fluid flows around the guide vanes 10 in the axial direction x, with the result that the inner ring or the individual inner ring segments 20 heat up, with the inner ring segments 20 heating up faster on their outside than on theirs due to the working fluid flowing directly past. facing away from the guide vanes 10 and the seal carrier segment 21 facing inside, which can lead to widening of gaps, in particular to widening of sealing gaps and consequently to leaks.
  • FIG. 3 shows a detail of a first exemplary embodiment of an inner ring segment 120 of a multi-part inner ring divided in the circumferential direction, according to the invention, in a perspective representation in a view from radially inside and 4 the inner ring segment 120 3 in view from radially inside.
  • the points in the Figures 3 and 4 The illustrated inner ring segment 120 of an inner ring designed according to the invention has a plurality of indentations 126, which are arranged evenly distributed in particular in the circumferential direction, are made in an inner circumferential surface of inner ring segment 120 and are only indicated in the illustration, with in particular exactly one indentation between two adjacent guide vane receptacles 124 of a pair of guide vane receptacles 124 is arranged.
  • the indentations 126 according to the invention reduce the cross-sectional area of the inner ring segment 120, in particular a wall thickness of the inner ring segment 120, locally.
  • an improved, transient heating behavior of the inner ring segment 120 and thus of the entire inner ring can advantageously be achieved, since less material of the inner ring has to be heated.
  • an improved, transient temperature profile can be achieved in the radial direction y, in particular a temperature profile with a lower temperature gradient in the radial direction y.
  • the depressions 126 have a greater extent in the axial direction x than in the circumferential direction. This results in a particularly advantageous thermal behavior of the inner ring or the inner ring segments 120 during operation of an associated turbomachine.
  • the depressions 126 each have a closed peripheral contour 127, with the peripheral contour in the region of its axial extension 127A and 127B running parallel, i.e. at a constant distance, to a peripheral contour of the guide vane receptacles 124 and in its sections 127C extending in the peripheral direction and 127D each runs parallel to a peripheral contour of the inner ring segment 120 .
  • the indentations 126 have in particular a substantially bone-shaped peripheral contour 127, based on a projection into a tangential plane of the inner ring segment 120.
  • the indentations 126 are also embodied symmetrically in the axial direction and extend, in particular locally, almost between two adjacent, in particular adjacent guide vane receptacles 124 completely over the area between these vane mounts 124.
  • figure 5 shows a section of a second inner ring segment 220 of a second exemplary embodiment of an inner ring according to the invention in a perspective representation.
  • 6 shows the inner ring segment 220 from figure 5 in another perspective view, this embodiment of an inner ring segment 220 of an inner ring according to the invention part of both in the circumferential direction as inner ring which is also divided in the axial direction x, with a partial plane running in the axial direction centrally through the guide vane receptacles 224 and the depressions 226 .
  • the depressions 226 which also have an essentially bone-shaped peripheral contour, but which is not specified in this case, can be seen particularly well.
  • the depressions 226 each have a bottom surface 228, the individual depressions 228 in this exemplary embodiment each having a constant depth T over almost the entire bottom surface 228 and thus a constant, local wall thickness in the region of the depressions 226.
  • FIG. 7 shows a section of a third exemplary embodiment of an inner ring according to the invention in a perspective view, with the depressions 326 in this exemplary embodiment extending over a smaller area due to the greater number and in particular closer arrangement of the guide vane receptacles 324, but otherwise being configured similarly to the exemplary embodiments described above.
  • All of the above-described exemplary embodiments of inner rings according to the invention have in common that the depressions 126, 226, 326, based on a functional installation state of the inner ring segments 120, 220, 320 or the associated inner rings, are each arranged on a side of the inner ring facing away from the guide vanes. in particular in an inner lateral surface of the inner ring. Furthermore, all depressions 126, 226, 326 have been introduced into the inner ring segments 120, 220, 320 by machining, in particular by milling.
  • depressions 126, 226, 326 lead to an advantageous weight reduction of the inner rings and thus also to a weight reduction of the turbomachine.

Description

Die vorliegende Erfindung betrifft einen Innenring für einen Leitschaufelkranz zur Befestigung an, insbesondere verstellbaren, Leitschaufeln einer Turbomaschine, insbesondere einer Verdichter- oder Turbinenstufe einer Gasturbine, einen Leitschaufelkranz und eine Turbomaschine, insbesondere Gasturbine, mit einem solchen Innenring sowie ein Verfahren zu dessen Herstellung.The present invention relates to an inner ring for a vane ring for attachment to, in particular adjustable, vanes of a turbomachine, in particular a compressor or turbine stage of a gas turbine, a vane ring and a turbomachine, in particular a gas turbine, with such an inner ring and a method for its production.

Beim Betrieb von Turbomaschinen mit derartigen Innenringen sind die Innenringe in der Regel thermischen Belastungen, insbesondere teilweise wechselnden und/oder hohen Temperaturgradienten, ausgesetzt, insbesondere durch das den Leitschaufelkranz durchströmende und damit den Innenring zumindest teilweise umströmende Arbeitsfluid und/oder durch schleifende Dichtungen zwischen dem Leitschaufelkranz und einem relativ zu diesem drehenden Rotor. Infolge der thermischen Belastung kann es zu unerwünschten, thermisch bedingten Verformungen des Innenrings kommen, insbesondere zum Aufweiten von Spalten und infolgedessen unerwünschten Leckagen, welche sich nachteilig auf den Wirkungsgrad der Turbomaschine auswirken können.During the operation of turbomachines with such inner rings, the inner rings are generally exposed to thermal loads, in particular partially changing and/or high temperature gradients, in particular due to the working fluid flowing through the guide vane ring and thus at least partially flowing around the inner ring and/or due to rubbing seals between the guide vane ring and a rotor rotating relative to this. As a result of the thermal stress, undesirable, thermally induced deformations of the inner ring can occur, in particular the widening of gaps and, as a result, undesirable leaks, which can have a disadvantageous effect on the efficiency of the turbomachine.

Gattungsgemäße Innenringe sind aus dem Stand der Technik grundsätzlich bekannt, beispielweise aus der FR 2 953 487 , wobei die FR 2 953 487 die Verwendung eines polygonförmigen Innenringes lehrt, welcher zwischen den Aufnahmen für die Leitschaufeln sich, bezogen auf den Innenring in einem funktionsgemäßen Einbauzustand in einer Turbomaschine, in radialer Richtung nach außen und in Umfangsrichtung erstreckende Verstärkungselemente, insbesondere Verstärkungsrippen, aufweist. Weitere Innenringe sind aus der EP 3 032 037 A1 , EP 31 76385 , DE 695 05 074 T2 und US 2015/275916 A1 bekannt.Generic inner rings are known in principle from the prior art, for example from FR 2 953 487 , where the FR 2 953 487 teaches the use of a polygonal inner ring which, relative to the inner ring in a functional installed state in a turbomachine, has reinforcing elements, in particular reinforcing ribs, extending in the radial direction outwards and in the circumferential direction between the receptacles for the guide vanes. More inner rings are from the EP 3 032 037 A1 , EP 31 76385 , DE 695 05 074 T2 and U.S. 2015/275916 A1 known.

In der EP 3 287 604 A2 wird ein Innenring beschrieben, der zwischen den Aufnahmen der Leitschaufeln vereinzelt schlitzförmige Aussparungen aufweist. Die Aussparungen dienen dazu, den Cording Effekt gezielt zu beeinflussen, in dem die Umfangsspannungen und der radiale Temperaturgradient beeinflusst wird. Nachteilig sind die Aussparungen schlitzförmig und sind nicht an die Kontur der Aussparungen für die Leitschaufeln angepasst, was für den Einsatzzweck der Erfindung nachteilig den umfänglichen Spannungsverlauf unterbricht und im Fuß der Schlitze zu Spannungsspitzen führen kann.In the EP 3 287 604 A2 an inner ring is described which has isolated slot-shaped recesses between the receptacles of the guide vanes. The cutouts serve to influence the cording effect in a targeted manner, in which the hoop stresses and the radial temperature gradient is affected. The disadvantage is that the recesses are slot-shaped and are not adapted to the contour of the recesses for the guide vanes, which for the purpose of the invention disadvantageously interrupts the circumferential stress profile and can lead to stress peaks in the base of the slots.

Eine Aufgabe einer Ausführung der vorliegenden Erfindung ist es, einen verbesserten Innenring bereitzustellen.An object of an embodiment of the present invention is to provide an improved inner ring.

Diese Aufgabe wird durch einen Innenring mit den Merkmalen des Anspruchs 1, durch einen Leitschaufelkranz gemäß Anspruch 11, durch eine Turbomaschine gemäß Anspruch 13, jeweils mit (wenigstens) einem hier beschriebenen Innenring, sowie durch ein Verfahren zum Herstellen eines hier beschriebenen Innenrings gemäß Anspruch 14 gelöst. Vorteilhafte Ausführungsformen der Erfindung sind Gegenstand der Unteransprüche.This object is achieved by an inner ring having the features of claim 1, by a vane ring according to claim 11, by a turbomachine according to claim 13, each with (at least) one inner ring described here, and by a method for producing an inner ring described here according to claim 14 solved. Advantageous embodiments of the invention are the subject matter of the dependent claims.

Nach einer Ausführung der vorliegenden Erfindung weist ein Innenring für einen Leitschaufelkranz zur Befestigung an, insbesondere verstellbaren, Leitschaufeln einer Turbomaschine, insbesondere einer Verdichter- oder Turbinenstufe einer Gasturbine, mehrere in Umfangrichtung jeweils beabstandet zueinander angeordnete Leitschaufelaufnahmen auf, insbesondere Ausnehmungen, welche jeweils zur Aufnahme eines Befestigungselementes, insbesondere eines Befestigungszapfens, einer Leitschaufel ausgebildet sind. Zwischen wenigstens zwei benachbarten Leitschaufelaufnahmen weist der Innenring dabei wenigstens eine Vertiefung mit einer in radialer Richtung reduzierten Wandstärke gegenüber einem an die Vertiefung angrenzenden Bereich außerhalb von der Vertiefung auf.According to one embodiment of the present invention, an inner ring for a guide vane ring for attachment to, in particular adjustable, guide vanes of a turbomachine, in particular a compressor or turbine stage of a gas turbine, has a plurality of guide vane receptacles arranged spaced apart from one another in the circumferential direction, in particular recesses, each of which is intended to accommodate a Fastening element, in particular a fastening pin, a vane are formed. Between at least two adjacent guide vane receptacles, the inner ring has at least one indentation with a wall thickness that is reduced in the radial direction compared to an area outside of the indentation that adjoins the indentation.

Erfindungsgemäß weist die Vertiefung, insbesondere die wenigstens eine Vertiefung, bezogen auf eine Rotationsachse einer Turbomaschine in einem funktionsgemäßen Einbauzustand des Innenrings in einer Turbomaschine, in axialer Richtung eine grö-ßere Ausdehnung auf als in Umfangsrichtung.According to the invention, the indentation, in particular the at least one indentation, has a greater extent in the axial direction than in the circumferential direction in relation to an axis of rotation of a turbomachine when the inner ring is functionally installed in a turbomachine.

Die Richtungsangabe "axial" bezieht sich vorliegend in fachüblicher Weise auf eine Richtung parallel zur Rotations- bzw. (Haupt)Maschinenachse der Turbomaschine, die Richtungsangabe "Umfangsrichtung" entsprechend auf eine Rotationsrichtung um diese Rotations- bzw. (Haupt)Maschinenachse, die Richtungsangabe "radial" auf eine Richtung, die senkrecht auf der axialen und Umfangsrichtung steht. Die Richtungsangabe "tangential" bezieht sich entsprechend auf eine Richtung, welche senkrecht auf der axialen Richtung und der radialen Richtung steht, wobei insbesondere sämtliche Richtungsangaben einen erfindungsgemäßen Innenring und/oder einen erfindungsgemäßen Leitschaufelkranz betreffend, jeweils auf einen funktionsgemäßen Einbauzustand in einer Turbomaschine bezogen sind.In the present case, the directional statement “axial” refers in a manner customary in the art to a direction parallel to the axis of rotation or (main) machine axis of the turbomachine, the directional statement “circumferential direction” correspondingly to a direction of rotation around this axis of rotation or (main) machine axis, the directional statement “ radial" to a direction perpendicular to the axial and circumferential directions. The directional statement "tangential" accordingly refers to a direction which is perpendicular to the axial direction and the radial direction, with all directional statements relating in particular to an inner ring according to the invention and/or a vane ring according to the invention being related to a functional installation state in a turbomachine.

"Leitschaufelaufnahmen" im Sinne der vorliegenden Erfindung sind insbesondere Ausnehmungen oder Aussparungen, insbesondere sacklochartige oder durchgehende Ausnehmungen oder Aussparungen, in denen Leitschaufeln radial abgestützt und/oder drehbar gelagert werden können."Guide vane receptacles" in the sense of the present invention are in particular recesses or recesses, in particular blind hole-like or continuous recesses or recesses in which guide vanes can be radially supported and/or rotatably mounted.

Unter einer "Vertiefung" im Sinne der vorliegenden Erfindung wird vorliegend insbesondere eine lokale Einkerbung oder Mulde oder dergleichen in radialer Richtung verstanden.A “depression” within the meaning of the present invention is understood here to mean in particular a local indentation or depression or the like in the radial direction.

Durch ein oder mehrere derartige Vertiefungen kann in einer Ausführung der vorliegenden Erfindung im Innenring eine verbesserte Temperaturverteilung, insbesondere ein vorteilhafteres Temperaturprofil in radialer Richtung, erreicht werden. Insbesondere kann durch die Vertiefung(en) eine thermisch bedingte Bewegung und/oder Deformation des Innenrings im Betrieb beeinflusst, insbesondere reduziert, werden, und so insbesondere eine Änderung seiner Form, insbesondere seines Durchmessers und/oder seiner Rundheit beeinflusst, insbesondere reduziert, werden.In one embodiment of the present invention, an improved temperature distribution, in particular a more advantageous temperature profile in the radial direction, can be achieved by one or more such depressions in the inner ring. In particular, the indentation(s) can influence, in particular reduce, a thermally induced movement and/or deformation of the inner ring during operation, and thus in particular a change in its shape, in particular its diameter and/or its roundness, can be influenced, in particular reduced.

Hierdurch kann in einer Ausführung der Erfindung insbesondere eine Dichtwirkung zwischen Leitschaufeln und Innenring im Bereich der Leitschaufelaufnahmen und/oder zwischen Leitschaufelkranz und Rotor und/oder ein Einlauf reduziert und so das Betriebsverhalten einer Turbomaschine, insbesondere ein Wirkungsgrad, verbessert werden.As a result, in one embodiment of the invention, a sealing effect between the guide vanes and the inner ring in the area of the guide vane mounts and/or between the guide vane ring and the rotor and/or an inlet can be reduced and the operating behavior of a turbomachine, in particular its efficiency, can be improved.

Durch ein oder mehrere derartige Vertiefungen kann in einer Ausführung der vorliegenden Erfindung insbesondere der sogenannte, unerwünschte "Cording-Effekt" reduziert werden.In one embodiment of the present invention, one or more such indentations can in particular reduce what is known as the undesired "cording effect".

Unter dem "Cording-Effekt" wird im Sinne der vorliegenden Erfindung eine dreidimensionale thermisch bedingte Deformation des Innenrings verstanden, insbesondere eine thermisch bedingte Ausbildung von Einschnürungen des Innenrings, welche insbesondere bei geteilten Innenringen an den Teilungsebenen auftreten können und welche insbesondere durch ein transientes, radiales Temperaturprofil infolge der unterschiedlichen Aufheizzeiten des Innenrings auf der Seite der Leitschaufeln, welche direkt vom Arbeitsfluid und damit schnell aufgeheizt wird, und der von den Leitschaufeln abgewandten Seite, langsam aufheizenden Seite, entstehen.In the context of the present invention, the "cording effect" is understood to mean a three-dimensional, thermally induced deformation of the inner ring, in particular a thermally induced formation of constrictions in the inner ring, which can occur at the dividing planes in particular in the case of divided inner rings and which are caused in particular by a transient, radial Temperature profile as a result of the different heating times of the inner ring on the side of the guide vanes, which is heated directly by the working fluid and thus quickly, and the side facing away from the guide vanes, which heats up slowly.

Durch die unterschiedlichen Aufheizzeiten des Innenrings auf der Seite der Leitschaufeln und der von den Leitschaufeln abgewandten Seite kann es zu unterschiedlichen, thermisch bedingten Ausdehnungen des Materials kommen, insbesondere zu einer stärkeren Ausdehnung des Materials auf der den Leitschaufeln zugewandten Seite als auf der von den Leitschaufeln abgewandten Seite und somit zu einer thermisch bedingten Deformation des Innenrings, ähnlich wie bei einem Bimetall. Infolge dieser Deformation kann es insbesondere zum Aufweiten von Spalten und infolgedessen zu unerwünschten Leckagen kommen, welche sich nachteilig auf den Wirkungsgrad der Turbomaschine auswirken können.The different heating times of the inner ring on the side of the guide vanes and the side facing away from the guide vanes can lead to different, thermally induced expansions of the material, in particular to a greater expansion of the material on the side facing the guide vanes than on the side facing away from the guide vanes Side and thus to a thermally induced deformation of the inner ring, similar to a bimetal. As a result of this deformation, gaps can in particular widen and, as a result, undesired leaks can occur, which can have a disadvantageous effect on the efficiency of the turbomachine.

Durch die erfindungsgemäße(n) Vertiefung(en) wird die Querschnittsfläche des Innenrings, insbesondere eine Wandstärke des Innenrings, insbesondere in radialer und/oder axialer Richtung und/oder in Umfangsrichtung, je nach Ausgestaltung der Vertiefung, lokal reduziert. Hierdurch kann in einer Ausführung der Erfindung vorteilhaft ein verbessertes, transientes Aufheizverhalten des Innenrings erreicht werden, da weniger Material des Innenrings aufgeheizt werden muss. Insbesondere kann in einer Ausführung der Erfindung ein verbessertes, transientes Temperaturprofil in radialer Richtung erreicht werden, insbesondere ein Temperaturprofil mit einem geringeren Temperaturgradienten in radialer Richtung, wodurch insbesondere bei geeigneter Ausgestaltung der Vertiefung(en), ein, in Bezug auf den "Cording-Effekt" verbessertes, insbesondere den "Cording-Effekt" reduzierendes, Aufheizverhalten des Innenrings erreicht werden.The indentation(s) according to the invention locally reduces the cross-sectional area of the inner ring, in particular a wall thickness of the inner ring, in particular in the radial and/or axial direction and/or in the circumferential direction, depending on the design of the indentation. In this way, in one embodiment of the invention, an improved, transient heating behavior of the inner ring can advantageously be achieved, since less material of the inner ring has to be heated. In particular, in one embodiment of the invention, an improved, transient temperature profile can be achieved in the radial direction, in particular a temperature profile with a lower temperature gradient in the radial direction, which, in particular with a suitable design of the recess(es), in relation to the "cording effect " improved heating behavior of the inner ring, in particular one that reduces the "cording effect".

Hierdurch wiederum kann bei einigen Ausführungen der vorliegenden Erfindung ein unerwünschtes Aufweiten von Spalten, insbesondere eine Ovalisierung der Leitschaufelaufnahmen, und/oder ein Einlaufen von Dichtfinnen in die eine Dichtstruktur eines Dichtungsträgers, reduziert oder sogar ganz vermieden werden, wodurch Leckagen reduziert und im Ergebnis der Wirkungsgrad der Turbomaschine verbessert und/oder ein spezifischer Treibstoffverbrauch gesenkt und/oder im Fall einer als Verdichter ausgebildeten Turbomaschine eine Pumpgrenze erhöht werden kann.As a result, in some embodiments of the present invention, an undesired widening of gaps, in particular an ovalization of the guide vane mounts, and/or sealing fins running into the one sealing structure of a seal carrier, can be reduced or even completely avoided, which reduces leakage and, as a result, the efficiency the turbomachine can be improved and/or a specific fuel consumption reduced and/or in the case of a turbomachine designed as a compressor a surge limit can be increased.

Unter einer "Pumpgrenze" wird im Sinne der vorliegenden Erfindung dabei ein zum Erreichen eines gewünschten Verdichtungsverhältnisses mindestens erforderliche stabile Volumenstrom verstanden, wobei mit zunehmenden Volumenstrom in der Regel eine höhere Verdichtung möglich ist.In the context of the present invention, a “surge limit” is understood to mean a stable volumetric flow that is at least required to achieve a desired compression ratio, with a higher compression being generally possible with an increasing volumetric flow.

Durch eine geringere Leckage lässt sich in einer Ausführung der Erfindung ein höherer, stabiler Volumenstrom erreichen. Hierdurch wiederum kann ein höheres Verdichtungsverhältnis erreicht werden, so dass eine Reduzierung von Leckagen im Ergebnis zu einem höheren Verdichtungsverhältnis führen kann.In one embodiment of the invention, a higher, more stable volume flow can be achieved due to a lower leakage. This in turn allows a higher compression ratio to be achieved, so that a reduction in leakage can result in a higher compression ratio.

Durch die infolge der erfindungsgemäße(n) Vertiefung(en) lokal reduzierte Wandstärke des Innenrings verringert sich ferner die Biegesteifigkeit des Innenrings, insbesondere in Umfangsrichtung, wodurch in einer Ausführung der Erfindung eine, insbesondere weitere, Verbesserung der "Cording-Eigenschaften", insbesondere eine (weitere) Reduzierung des "Cording-Effekts", erreicht werden kann.The wall thickness of the inner ring, which is locally reduced as a result of the depression(s) according to the invention, also reduces the flexural rigidity of the inner ring, in particular in the circumferential direction, which, in one embodiment of the invention, results in one, in particular further, improvement in the "cording properties", in particular a (further) reduction of the "cording effect" can be achieved.

Insbesondere kann auf diese Weise ein Leitschaufelkranz mit einem biegeweicheren Innenring und einem biegesteiferen Dichtungsträger bereitgestellt werden, mit welchem besonders gut der "Cording-Effekt" reduziert werden kann, wie sich herausgestellt hat.In particular, a vane ring with a more flexible inner ring and a more rigid seal carrier can be provided in this way, with which the "cording effect" can be reduced particularly well, as has been found.

Ferner kann durch die erfindungsgemäße(n) Vertiefung(en) eine Gewichtsreduktion des Innenrings und damit eines Leitschaufelkranzes sowie einer Turbomaschine erreicht werden.Furthermore, the weight of the inner ring and thus of a ring of guide vanes and a turbomachine can be reduced by the indentation(s) according to the invention.

Die vorliegende Erfindung weist wenigstens eine Vertiefung mit einer sanduhrförmigen oder sanduhrformartigen Umfangskontur auf, insbesondere bezogen auf eine Projektion der Umfangskontur der Vertiefung in eine Tangentialebene des Innenrings. Es hat sich herausgestellt, dass hierdurch ein besonders vorteilhaftes thermisches Verhalten des Innenrings erreicht werden kann, insbesondere eine besonders vorteilhafte thermische Bewegung und/oder Deformation des Innenrings, insbesondere eine thermisch bedingte Bewegung/Deformation des Innenrings, welche zu einer besonders geringen Abweichung von der Rundheit, insbesondere zu einer besonders geringen Ovalisierung, des Innenrings und/oder der Leitschaufelaufnahmen führt.The present invention has at least one depression with an hourglass-shaped or hourglass-like peripheral contour, in particular based on a projection of the peripheral contour of the depression into a tangential plane of the inner ring. It has been found that a particularly advantageous thermal behavior of the inner ring can be achieved in this way, in particular a particularly advantageous thermal movement and/or deformation of the inner ring, in particular a thermally induced movement/deformation of the inner ring, which leads to a particularly small deviation from roundness , In particular, leads to a particularly low degree of ovalization of the inner ring and/or the vane mounts.

In einer Ausführung der vorliegenden Erfindung ist der Innenring insbesondere derart ausgestaltet, insbesondere die Vertiefungen des Innenrings, dass der Innenring gegenüber einem Innenring ohne Vertiefungen eine um wenigstens 10%, insbesondere um wenigstens oder um etwa 15% reduzierte Biegesteifigkeit, insbesondere in Umfangsrichtung, aufweist.In one embodiment of the present invention, the inner ring is designed in particular in such a way, in particular the indentations of the inner ring, that the inner ring has a bending stiffness that is reduced by at least 10%, in particular by at least or around 15%, in particular in the circumferential direction, compared to an inner ring without indentations.

In einer Ausführung der vorliegenden Erfindung weist der Innenring insbesondere mehrere Vertiefungen auf, insbesondere mehrere, jeweils auf einer von den Leitschaufeln abgewandten Seite des Innenrings angeordnete Vertiefungen, wobei die Vertiefungen, insbesondere wenigsten im Wesentlichen äquidistant, über den Umfang des Innenrings verteilt angeordnet sind.In one embodiment of the present invention, the inner ring has in particular a plurality of indentations, in particular a plurality of indentations each arranged on a side of the inner ring facing away from the guide vanes, the indentations being distributed, in particular at least substantially equidistantly, over the circumference of the inner ring.

Hierdurch kann in einer Ausführung der vorliegenden Erfindung ein besonders vorteilhaftes Aufheizverhalten und/oder eine vorteilhafte Reduktion der Biegesteifigkeit des Innenrings erreicht werden.In this way, in one embodiment of the present invention, a particularly advantageous heating behavior and/or an advantageous reduction in the flexural rigidity of the inner ring can be achieved.

In einer Ausführung der vorliegenden Erfindung ist insbesondere wenigstens zwischen zwei benachbarten Leitschaufelaufnahmen oder benachbarten Gruppen von Leitschaufelaufnahmen genau eine Vertiefung vorgesehen, insbesondere jeweils.In one embodiment of the present invention, exactly one depression is provided at least between two adjacent guide vane mounts or adjacent groups of guide vane mounts, in particular in each case.

D.h. mit anderen Worten, dass in einer Ausführung der Erfindung der Innenring insbesondere zwischen wenigstens einem Paar von benachbarten Paar von Leitschaufelaufnahmen oder einem Paar von benachbarten Gruppen von Leitschaufelaufnahmen genau eine Vertiefung aufweist, insbesondere jeweils zwischen zwei Leitschaufelaufnahmen oder zwei Gruppen von Leitschaufelaufnahmen genau eine Vertiefung.In other words, in one embodiment of the invention, the inner ring has exactly one indentation, in particular between at least one pair of adjacent pairs of guide vane mounts or a pair of adjacent groups of guide vane mounts, in particular between two guide vane mounts or two groups of guide vane mounts exactly one indentation.

Hierdurch kann in einer Ausführung der vorliegenden Erfindung ein besonders vorteilhaftes Aufheizverhalten und/oder eine vorteilhafte Reduktion der Biegesteifigkeit des Innenrings erreicht werden, insbesondere ein vorteilhaftes, insbesondere gleichmäßigeres, Aufheizverhalten über den gesamten Umfang des Innenrings bzw. eine gleichmäßige(re) Biegesteifigkeit des Innenrings in Umfangsrichtung.As a result, in one embodiment of the present invention, a particularly advantageous heating behavior and/or an advantageous reduction in the flexural rigidity of the inner ring can be achieved, in particular an advantageous, in particular more uniform, heating behavior over the entire circumference of the inner ring or a (more) uniform flexural rigidity of the inner ring circumferential direction.

In einer Ausführung der vorliegenden Erfindung ist insbesondere wenigstens eine Vertiefung, bezogen auf einen funktionsgemäßen Einbauzustand des Innenrings in einer Turbomaschine, auf einer von den Leitschaufeln abgewandten Seite des Innenrings angeordnet, insbesondere in einer in radialer Richtung innenliegenden Fläche des Innenrings, insbesondere in einer inneren Mantelfläche des Innenrings.In one embodiment of the present invention, in particular at least one indentation, based on a functional installation state of the inner ring in a turbomachine, is arranged on a side of the inner ring facing away from the guide vanes, in particular in a surface of the inner ring lying on the inside in the radial direction, in particular in an inner lateral surface of the inner ring.

Hierdurch kann in einer Ausführung der vorliegenden Erfindung insbesondere ein schnelleres Aufheizen der Innenseite des Innenrings und infolgedessen eine im Hinblick auf den "Cording-Effekt" besonders vorteilhafte Temperaturverteilung in radialer Richtung erreicht werden, insbesondere ein schnelleres Aufheizen der von den Leitschaufeln abgewandten Seite des Innenrings, bezogen auf einen funktionsgemä-ßen Einbauzustand in einer Turbomaschine.In this way, in one embodiment of the present invention, in particular faster heating of the inside of the inner ring and, as a result, a temperature distribution in the radial direction that is particularly advantageous with regard to the "cording effect" can be achieved, in particular faster heating of the side of the inner ring facing away from the guide vanes, based on a functional installation state in a turbomachine.

In einer alternativen, insbesondere zusätzlichen, Ausführung der vorliegenden Erfindung kann der Innenring auch wenigstens eine, in eine, eine den Leitschaufeln zugewandte Fläche des Innenrings eingebracht sein.In an alternative, in particular additional, embodiment of the present invention, the inner ring can also be introduced into at least one surface of the inner ring facing the guide vanes.

In einer Ausführung der vorliegenden Erfindung verläuft die Umfangskontur wenigstens einer Vertiefung insbesondere zumindest teilweise parallel zu einer Umfangskontur einer benachbarten Ausnehmung, insbesondere in einem sich im Wesentlichen in axialer Richtung des Innenrings erstreckenden Bereich der Umfangskontur, bezogen auf einen funktionsgemäßen Einbauzustand in einer Turbomaschine, wobei die Umfangskontur insbesondere zumindest teilweise parallel zu den Umfangskonturen beider benachbarter Ausnehmungen verläuft. Hierdurch kann ein besonders vorteilhaftes thermisches Verhalten des Innenrings erreicht werden. Vorteilhaft ergeben sich hierdurch zwischen den Vertiefungen und den Ausnehmungen Abgrenzungsstege, die insbesondere, vorzugsweise zumindest teilweise, entlang ihrer Längserstreckung eine konstante Dicke aufweisen können.In one embodiment of the present invention, the peripheral contour of at least one depression runs in particular at least partially parallel to a peripheral contour of an adjacent recess, in particular in an area of the peripheral contour that extends essentially in the axial direction of the inner ring, based on a functional installation state in a turbomachine, wherein the peripheral contour runs in particular at least partially parallel to the peripheral contours of both adjacent recesses. As a result, a particularly advantageous thermal behavior of the inner ring can be achieved. This advantageously results in delimiting webs between the indentations and the recesses, which in particular, preferably at least partially, can have a constant thickness along their longitudinal extent.

Unter dem Ausdruck "parallel" wird dabei im Sinne der vorliegenden Erfindung, insbesondere im Zusammenhang mit der Umfangskontur einer Vertiefung, "mit konstantem Abstand" verstanden.The expression "parallel" is understood in the context of the present invention, in particular in connection with the peripheral contour of a depression, as "at a constant distance".

In einer Ausführung der vorliegenden Erfindung verläuft die Umfangskontur wenigstens einer Vertiefung insbesondere zumindest teilweise parallel zu einer Kontur des Innenrings in Umfangsrichtung des Innenrings, insbesondere in einem sich im Wesentlichen in Umfangsrichtung des Innenrings erstreckenden Bereich der Umfangskontur, bezogen auf einen funktionsgemäßen Einbauzustand in einer Turbomaschine. Hierdurch kann ein besonders vorteilhaftes thermisches Verhalten des Innenrings erreicht werden.In one embodiment of the present invention, the peripheral contour of at least one depression runs in particular at least partially parallel to a contour of the inner ring in the peripheral direction of the inner ring, in particular in a region of the peripheral contour that extends essentially in the peripheral direction of the inner ring, based on a functional installation state in a turbomachine. As a result, a particularly advantageous thermal behavior of the inner ring can be achieved.

In einer Ausführung der vorliegenden Erfindung ist die Umfangskontur dabei insbesondere symmetrisch oder asymmetrisch in und/oder zu einer axialen Richtung ausgebildet.In one embodiment of the present invention, the peripheral contour is in particular embodied symmetrically or asymmetrically in and/or with respect to an axial direction.

Unter einer "Tangentialebene" wird im Sinne der vorliegenden Erfindung eine senkrecht zur radialen Richtung stehende Ebene verstanden, insbesondere eine sich senkrecht zu einem zugehörigen Radius erstreckende Ebene.In the context of the present invention, a “tangential plane” is understood to mean a plane that is perpendicular to the radial direction, in particular a plane that extends perpendicular to an associated radius.

In einer Ausführung der vorliegenden Erfindung weist insbesondere wenigstens eine Vertiefung eine vollständig geschlossene oder an wenigstens einem axialen Ende, insbesondere nur an einem axialen Ende, offene Umfangskontur auf. Eine Vertiefung mit an ihren axialen Enden offenen Umfangskontur lässt sich besonders einfach herstellen, insbesondere durch Zerspanen. Eine Vertiefung mit einer vollständig geschlossenen Umfangskontur führt in der Regel zu einer geringeren Leckage als eine vergleichbare Vertiefung mit einer an einem axialen Ende offenen Umfangskontur, da insbesondere die an den axialen Enden geschlossene Umfangskontur ein Strömen des Arbeitsfluids von der Leitschaufelseite durch das offene Ende in die Vertiefung auf die von den Leitschaufeln abgewandte Seite des Innenrings reduziert bzw. verhindert.In one embodiment of the present invention, in particular at least one depression has a peripheral contour that is completely closed or open at at least one axial end, in particular only at one axial end. A depression with a peripheral contour that is open at its axial ends can be produced particularly easily, in particular by machining. A depression with a completely closed peripheral contour generally leads to less leakage than a comparable depression with a peripheral contour that is open at one axial end, since, in particular, the peripheral contour closed at the axial ends reduces or prevents the working fluid from flowing from the guide vane side through the open end into the depression on the side of the inner ring facing away from the guide vanes.

In einer Ausführung der vorliegenden Erfindung weist insbesondere wenigstens eine Vertiefung eine Bodenfläche auf, wobei die Vertiefung insbesondere wenigstens im Bereich der Bodenfläche zumindest teilweise, insbesondere über die gesamte Bodenfläche, eine konstante Tiefe aufweist, insbesondere derart, dass der Innenring im Bereich der Bodenfläche insbesondere eine konstante Wandstärke aufweist und/oder eine Innenkontur mit konstantem Radius bezogen auf die (Haupt-)Maschinenachse bzw. die Rotationsachse der Turbomaschine bezogen auf einen funktionsgemäßen Einbauzustand des Innenrings in einer Turbomaschine. Hierdurch kann auf besonders einfache Art und Weise eine effektive Wandstärkenreduzierung erreicht werden, insbesondere bei gleichzeitigem vorteilhaftem thermischen Verhalten des Innenrings.In one embodiment of the present invention, in particular at least one indentation has a bottom surface, with the indentation having a constant depth, in particular at least in the area of the bottom surface, at least partially, in particular over the entire bottom surface, in particular such that the inner ring in the area of the bottom surface has in particular a has a constant wall thickness and/or an inner contour with a constant radius in relation to the (main) machine axis or the axis of rotation of the turbomachine in relation to a functional installation state of the inner ring in a turbomachine. As a result, an effective wall thickness reduction can be achieved in a particularly simple manner, in particular with simultaneous advantageous thermal behavior of the inner ring.

In einer Ausführung der vorliegenden Erfindung ist die Tiefe wenigstens einer Vertiefung dabei so groß wie möglich gewählt und infolgedessen die Wandstärke insbesondere lokal im Bereich der Vertiefung und/oder in einem an die Vertiefung angrenzenden Bereich minimiert.In one embodiment of the present invention, the depth of at least one indentation is selected to be as large as possible and as a result the wall thickness is minimized, particularly locally in the area of the indentation and/or in an area adjoining the indentation.

In einer Ausführung der vorliegenden Erfindung ist der Innenring einteilig ausgebildet. In einer anderen Ausführung der vorliegenden Erfindung ist der Innenring mehrteilig ausgebildet, insbesondere in Umfangsrichtung und/oder in axialer Richtung geteilt.In one embodiment of the present invention, the inner ring is designed in one piece. In another embodiment of the present invention, the inner ring is designed in multiple parts, in particular divided in the circumferential direction and/or in the axial direction.

Ist der Innenring in einer Ausführung der vorliegenden Erfindung in Umfangsrichtung geteilt, weist er insbesondere mehrere Innenringsegmente auf und ist insbesondere aus mehreren Innenringsegmenten zusammengesetzt, insbesondere aus wenigstens zwei Innenringsegmenten, welche sich in diesem Fall vorzugsweise jeweils über einen Umfangswinkel von etwa, insbesondere genau, 180° erstrecken oder aus drei Innenringsegmenten, die sich vorzugsweise jeweils über einen Umfangswinkel von etwa, insbesondere genau, 120° erstrecken. In einer Weiterbildung dieser Ausführung sind in einer Ausführung der vorliegenden Erfindung dabei insbesondere jeweils zwei in Umfangsrichtung aneinandergrenzende Innenringsegmente dabei an ihren Stoßflächen insbesondere mithilfe wenigstens eines, sich in Umfangsrichtung erstreckenden Verbindungszapfens oder -stiftes miteinander gekoppelt, insbesondere verbunden.If, in one embodiment of the present invention, the inner ring is divided in the circumferential direction, it has in particular several inner ring segments and is in particular composed of several inner ring segments, in particular of at least two inner ring segments, which in this case preferably each extend over a circumferential angle of approximately, in particular exactly, 180 ° extend or from three inner ring segments, which preferably each extend over a circumferential angle of about, in particular exactly, 120 °. In a further development of this embodiment, in one embodiment of the present invention, in particular two inner ring segments adjoining one another in the circumferential direction are coupled, in particular connected, to one another at their abutting surfaces, in particular with the aid of at least one connecting pin or connecting pin extending in the circumferential direction.

Alternativ oder zusätzlich zu einer Teilung in Umfangsrichtung kann der Innenring bzw. wenigstens ein Innenringsegment in axialer Richtung geteilt sein, wobei sich die Teilung insbesondere über die gesamte Länge des Innenrings bzw. des Innenringsegments in Umfangsrichtung erstreckt und insbesondere in einer gemeinsamen Radialebene durch den Innenring bzw. das zugehörige Innenringsegment verläuft. In einer Weiterbildung dieser Ausführung sind in einer Ausführung der vorliegenden Erfindung dabei die einzelnen Innenringteile mithilfe wenigstens eines, sich in axialer Richtung erstreckenden Verbindungszapfens - oder -stiftes miteinander gekoppelt, insbesondere verbunden.As an alternative or in addition to a division in the circumferential direction, the inner ring or at least one inner ring segment can be divided in the axial direction, with the division extending in particular over the entire length of the inner ring or the inner ring segment in the circumferential direction and in particular in a common radial plane through the inner ring or The associated inner ring segment runs. In a development of this embodiment, in one embodiment of the present invention, the individual inner ring parts are coupled, in particular connected, to one another with the aid of at least one connecting pin or pin extending in the axial direction.

In einer Ausführung der vorliegenden Erfindung ist insbesondere wenigstens eine Vertiefung, insbesondere sämtliche Vertiefungen, durch ein trennendes Fertigungsverfahren in den Innenring eingebracht worden, insbesondere durch eine mechanische Bearbeitung, insbesondere durch Zerspanen, insbesondere durch Spanen mit geometrisch bestimmter Schneide, insbesondere durch Fräsen. Auf diese Art und Weise können die Vertiefungen besonders einfach in den Innenring eingebracht werden. Insbesondere lassen sich auf diese Art und Weise besonders einfache und präzise Vertiefungen einbringen.In one embodiment of the present invention, at least one indentation, in particular all indentations, has been made in the inner ring by a separating manufacturing process, in particular by mechanical processing, in particular by machining, in particular by machining with a geometrically defined cutting edge, in particular by milling. In this way, the depressions can be introduced into the inner ring in a particularly simple manner. In particular, particularly simple and precise indentations can be introduced in this way.

Ein erfindungsgemäßer Leitschaufelkranz für eine Turbomaschine, insbesondere eine Verdichter- oder Turbinenstufe einer Gasturbine mit einem Innenring und, insbesondere verstellbaren, Leitschaufeln, an denen der Innenring befestigt ist, weist einen vorbeschrieben gemäß der vorliegenden Erfindung ausgebildeten Innenring auf.A ring of guide vanes according to the invention for a turbomachine, in particular a compressor or turbine stage of a gas turbine with an inner ring and, in particular, adjustable guide vanes to which the inner ring is attached, has an inner ring designed according to the present invention as described above.

In einer Ausführung der vorliegenden Erfindung ist wenigstens eine Leitschaufel mittels eines sich in radialer Richtung erstreckenden Befestigungszapfen, der in eine korrespondierend ausgebildete Leitschaufelaufnahme des Innenrings eingesteckt ist, mit dem Innenring verbunden, insbesondere in radialer Richtung am Innenring abgestützt, insbesondere drehbar um eine Längsachse im Innenring gelagert. Vorzugsweise ist zwischen dem Innenring und dem Befestigungszapfen ferner eine Aufnahmebuchse vorgesehen.In one embodiment of the present invention, at least one guide vane is connected to the inner ring by means of a fastening pin that extends in the radial direction and is inserted into a correspondingly designed guide vane receptacle of the inner ring, in particular supported on the inner ring in the radial direction, in particular rotatable about a longitudinal axis in the inner ring stored. Preferably a receiving bushing is also provided between the inner ring and the mounting pin.

In einer Ausführung der vorliegenden Erfindung weist der Leitschaufelkranz insbesondere zusätzlich einen Dichtungsträger oder ein Dichtungsträgersegment auf, wobei der Dichtungsträger oder das Dichtungsträgersegment insbesondere auf der von den Leitschaufeln abgewandten Seite angeordnet ist und insbesondere wenigstens eine in einer von den Leitschaufeln abgewandten Fläche angeordnete Vertiefung zumindest teilweise, insbesondere vollständig, abdeckt.In one embodiment of the present invention, the vane ring has in particular an additional seal carrier or a seal carrier segment, the seal carrier or the seal carrier segment being arranged in particular on the side facing away from the guide vanes and in particular at least one depression arranged in a surface remote from the guide vanes, at least partially, in particular completely covers.

Eine erfindungsgemäße Turbomaschine, insbesondere Gasturbine, mit wenigstens einer Verdichter- oder Turbinenstufe mit einem Innenring weist einen vorbeschrieben gemäß der vorliegenden Erfindung ausgebildeten Innenring auf.A turbomachine according to the invention, in particular a gas turbine, with at least one compressor or turbine stage with an inner ring has an inner ring designed according to the present invention as described above.

In einer Ausführung der vorliegenden Erfindung weist eine Turbomaschine insbesondere eine oder mehrere Verdichter- und/oder Turbinenstufen auf. Eine oder mehrere dieser Verdichter- und oder Turbinenstufen weisen insbesondere jeweils ein Lauf- und ein Leitgitter auf, wobei insbesondere eines oder mehrere dieser Leitgitter einen erfindungsgemäßen Leitschaufelkranz aufweisen.In one embodiment of the present invention, a turbomachine has, in particular, one or more compressor and/or turbine stages. In particular, one or more of these compressor and/or turbine stages each have a rotor cascade and a guide cascade, with one or more of these guide cascades in particular having a guide vane ring according to the invention.

In einer besonders vorteilhaften Ausgestaltung wird die Erfindung in Gasturbinen, insbesondere in Gasturbinentriebwerken, insbesondere in einem Hochdruckund/oder Niederdruckverdichter verwendet.In a particularly advantageous embodiment, the invention is used in gas turbines, in particular in gas turbine engines, in particular in a high-pressure and/or low-pressure compressor.

In einer Ausführung der vorliegenden Erfindung ist die Turbomaschine daher insbesondere ein Verdichter, insbesondere ein Hochdruck- oder Niederdruckverdichter.In one embodiment of the present invention, the turbomachine is therefore in particular a compressor, in particular a high-pressure or low-pressure compressor.

Ein erfindungsgemäßer Innenring wird in einer Ausführung eines Verfahrens gemäß der vorliegenden Erfindung hergestellt, indem wenigstens eine Vertiefung des Innenrings, insbesondere sämtliche Vertiefungen, durch ein trennendes Fertigungsverfahren hergestellt wird, insbesondere durch eine mechanische Bearbeitung, insbesondere durch Zerspanen, insbesondere durch Spanen mit geometrisch bestimmter Schneide, insbesondere durch Fräsen.An inner ring according to the invention is produced in one embodiment of a method according to the present invention in that at least one indentation of the inner ring, in particular all indentations, is produced by a separating manufacturing process, in particular by mechanical processing, in particular by machining, in particular by machining with a geometrically defined cutting edge , especially by milling.

Weitere vorteilhafte Weiterbildungen der vorliegenden Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung bevorzugter Ausführungen. Hierzu zeigen, teilweise schematisiert:

Fig. 1
einen Ausschnitt eines Leitschaufelkranzsegments einer als Verdichter ausgebildeten, aus dem Stand der Technik bekannten Turbomaschine im Bereich eines Innenrings in Seitenansicht,
Fig. 2
einen Ausschnitt des Leitschaufelkranzsegmentes aus Fig. 1 in perspektivischer Darstellung,
Fig. 3
einen Ausschnitt eines ersten Ausführungsbeispiels eines Innenringsegments eines erfindungsgemäßen Innenrings in perspektivischer Darstellung in Ansicht von radial innen,
Fig. 4
das Innenringsegment aus Fig. 3 in Ansicht von radial innen,
Fig. 5
einen Ausschnitt eines Innenringsegments eines zweiten Ausführungsbeispiels eines erfindungsgemäßen Innenrings in perspektivischer Darstellung,
Fig. 6
das Innenringsegment aus Fig. 5 in einer anderen perspektivischen Darstellung und
Fig. 7
einen Ausschnitt eines dritten Ausführungsbeispiels eines erfindungsgemäßen Innenrings in perspektivischer Darstellung.
Further advantageous developments of the present invention result from the dependent claims and the following description of preferred embodiments. Show, partially schematized:
1
a section of a vane ring segment of a turbomachine designed as a compressor and known from the prior art in the area of an inner ring in a side view,
2
a section of the vane ring segment 1 in perspective view,
3
a section of a first exemplary embodiment of an inner ring segment of an inner ring according to the invention in a perspective view viewed from radially inside,
4
the inner ring segment 3 in view from radially inside,
figure 5
a section of an inner ring segment of a second embodiment of an inner ring according to the invention in a perspective view,
6
the inner ring segment figure 5 in a different perspective view and
7
a section of a third embodiment of an inner ring according to the invention in a perspective view.

Fig. 1 zeigt zum besseren Verständnis der Erfindung einen Ausschnitt eines gattungsgemäßen, aus dem Stand der Technik bekannten Leitschaufelkranzsegments 1 einer als Verdichter ausgebildeten, aus dem Stand der Technik bekannten Turbomaschine mit einem Innenringsegment 20 im Bereich des Innenringsegments 20 in Seitenansicht. 1 shows a section of a generic vane ring segment 1 known from the prior art of a turbomachine designed as a compressor known from the prior art with an inner ring segment 20 in the region of the inner ring segment 20 in a side view for a better understanding of the invention.

Das Innenringsegment 20 ist in aus dem Stand der Technik bekannter Weise an den Leitschaufeln 10 befestigt, wobei das Innenringsegment 20 dazu in Umfangsrichtung gleichmäßig verteilt angeordnete, insbesondere als Durchgangsöffnungen ausgebildete, Leitschaufelaufnahmen 24 aufweist, wobei die Leitschaufeln 10 über sich in radialer Richtung y erstreckende Befestigungszapfen 11 mit dem Innenringsegment 20 verbunden sind und in radialer Richtung am Innenringsegment 20 abgestützt sind.The inner ring segment 20 is fastened to the guide vanes 10 in a manner known from the prior art, with the inner ring segment 20 having guide vane receptacles 24 distributed uniformly in the circumferential direction, in particular designed as through-openings, the guide vanes 10 having fastening pins extending in the radial direction y 11 are connected to the inner ring segment 20 and are supported on the inner ring segment 20 in the radial direction.

In diesem Fall sind die Leitschaufeln 10 verstellbar ausgebildet und drehbar um eine Längsachse L mit dem Innenringsegment 20 verbunden. Zur Minimierung der Reibung zwischen Befestigungszapfen 11 und Innenringsegment 20 ist jeweils eine Buchse 25 in die Durchgangsöffnung für die Leitschaufelaufnahme 24 eingebracht.In this case, the guide vanes 10 are designed to be adjustable and are connected to the inner ring segment 20 so as to be rotatable about a longitudinal axis L. In order to minimize the friction between the fastening pin 11 and the inner ring segment 20 , a bushing 25 is introduced into the passage opening for the guide vane mount 24 .

Zur Abdichtung gegenüber dem drehbar gelagerten Rotor 30 der Turbomaschine weist der Leitschaufelkranz 1 ferner ein auf einer von den Leitschaufeln 10 abgewandten Seite am Innenringsegment 20 befestigtes Dichtungsträgersegment 21 auf, wobei das Dichtungsträgersegment 21 ebenfalls in bekannter Weise am Innenringsegment 20 angeordnet ist, wobei in diesem Fall, insbesondere zugunsten einer hohen Dichtwirkung, die als Durchgangsöffnungen ausgebildeten Leitschaufelaufnahmen 24 auf einer von den Leitschaufeln 10 abgewandten Seite des Innenrings durch das Dichtungsträgersegment 21 abdeckt sind.For sealing against the rotatably mounted rotor 30 of the turbomachine, the guide vane ring 1 also has a seal carrier segment 21 fastened to the inner ring segment 20 on a side facing away from the guide vanes 10, with the seal carrier segment 21 also being arranged in a known manner on the inner ring segment 20, with in this case , in particular for the benefit of a high sealing effect, the guide vane receptacles 24 embodied as through openings are covered by the seal carrier segment 21 on a side of the inner ring facing away from the guide vanes 10 .

Für eine weitere Verbesserung der Dichtwirkung ist an einer radialen Innenseite des Dichtungsträgersegments 21 eine Dichtstruktur 22, insbesondere eine honigwabenförmige Dichtstruktur 22, vorgesehen, welche mit am Rotor befestigten, sich in radialer Richtung vom Rotor nach außen erstreckenden, sogenannten Dichtfinnen 31 zusammenwirkt und einen Spalt zwischen dem Gehäuse fest angeordneten Leitschaufelkranz bzw. Leitschaufelkranzsegment 1 und dem drehbar gelagerten Rotor 30 der Turbomaschine abdichtet, um Strömungsverluste durch Leckagen beim Umströmen der Leitschaufeln 10, insbesondere eine Reduzierung des Volumenstroms im Bereich der Leitschaufeln 10, zu reduzieren.To further improve the sealing effect, a sealing structure 22, in particular a honeycomb-shaped sealing structure 22, is provided on a radial inner side of the seal carrier segment 21, which interacts with so-called sealing fins 31, which are fastened to the rotor and extend outwards in the radial direction from the rotor, and which creates a gap between the guide vane ring or guide vane ring segment 1 fixedly arranged on the housing and the rotatably mounted rotor 30 of the turbomachine in order to reduce flow losses due to leaks when flowing around the guide vanes 10, in particular a reduction in the volume flow in the area of the guide vanes 10.

Das Leitschaufelkranzsegment 1 ist dabei Teil eines Leitschaufelkranzes, welcher in Umfangsrichtung in mehrere Leitschaufelkranzsegmente 1 unterteilt ist, wobei jedes Leitschaufelkranzsegment 1 ein Innenringsegment 20 und ein entsprechendes Dichtungsträgersegment 21 aufweist. Zur Verbindung der einzelnen Leitschaufelkranzsegmente in Umfangsrichtung miteinander, insbesondere zur Verbindung der einzelnen Innenringsegmente 20 in Umfangsrichtung miteinander, weist jedes Innenringsegment 20 an einer seiner Stirnseiten in Umfangsrichtung einen Verbindungszapfen 23 auf und an der anderen Stirnseite eine hier nicht dargestellte, entsprechend zum Verbindungszapfen 23 korrespondierend ausgebildete Ausnehmung.The vane ring segment 1 is part of a vane ring, which is divided in the circumferential direction into several vane ring segments 1, each Guide vane ring segment 1 has an inner ring segment 20 and a corresponding seal carrier segment 21 . In order to connect the individual guide vane ring segments to one another in the circumferential direction, in particular to connect the individual inner ring segments 20 to one another in the circumferential direction, each inner ring segment 20 has a connecting pin 23 on one of its end faces in the circumferential direction and a connecting pin 23 on the other end face, which is not shown here and is designed to correspond to the connecting pin 23 recess.

Fig. 2 zeigt einen Ausschnitt des Leitschaufelkranzsegmentes aus Fig. 1 in perspektivischer Darstellung, wobei in dieser Darstellung insbesondere gut der Verbindungszapfen 23 an der Stirnseite des Innenringsegments 20, die als Durchgangsöffnungen ausgebildeten Leitschaufelaufnahmen 24 sowie die in den Durchgangsöffnungen für die Leitschaufelaufnahmen 24 angeordneten Buchsen 25 erkennbar sind. 2 shows a section of the vane ring segment 1 in a perspective representation, in this representation the connecting pin 23 on the end face of the inner ring segment 20, the guide vane receptacles 24 designed as through-openings and the bushings 25 arranged in the through-openings for the guide vane receptacles 24 can be seen particularly well.

Beim Betrieb der Turbomaschine werden die Leitschaufeln 10 in axialer Richtung x von einem Arbeitsfluid umströmt, wobei sich infolgedessen der Innenring bzw. die einzelnen Innenringsegmente 20 aufheizen, wobei sich die Innenringsegmente 20 auf ihrer Außenseite dabei durch das unmittelbar vorbeiströmende Arbeitsfluid schneller aufheizen als an ihrer, von den Leitschaufeln 10 abgewandten und dem Dichtungsträgersegment 21 zugewandten Innenseite, wodurch es zum Aufweiten von Spalten, insbesondere zum Aufweiten von Dichtspalten und infolgedessen zu Leckagen kommen kann.During operation of the turbomachine, a working fluid flows around the guide vanes 10 in the axial direction x, with the result that the inner ring or the individual inner ring segments 20 heat up, with the inner ring segments 20 heating up faster on their outside than on theirs due to the working fluid flowing directly past. facing away from the guide vanes 10 and the seal carrier segment 21 facing inside, which can lead to widening of gaps, in particular to widening of sealing gaps and consequently to leaks.

Fig. 3 zeigt einen Ausschnitt eines ersten Ausführungsbeispiels eines Innenringsegments 120 eines mehrteiligen, in Umfangsrichtung geteilten, erfindungsgemäßen Innenrings in perspektivischer Darstellung in Ansicht von radial innen und Fig. 4 das Innenringsegment 120 aus Fig. 3 in Ansicht von radial innen. Dabei weist das in den Fig. 3 und 4 dargestellte Innenringsegment 120 eines erfindungsgemäß ausgebildeten Innenrings mehrere, insbesondere in Umfangsrichtung gleichmäßig verteilt angeordnete, in eine innere Mantelfläche des Innenringsegments 120 eingebrachte, in der Darstellung nur angedeutete Vertiefungen 126 auf, wobei insbesondere jeweils genau eine Vertiefung zwischen zwei benachbarten Leitschaufelaufnahmen 124 eines Paares von Leitschaufelaufnahmen 124 angeordnet ist. 3 shows a detail of a first exemplary embodiment of an inner ring segment 120 of a multi-part inner ring divided in the circumferential direction, according to the invention, in a perspective representation in a view from radially inside and 4 the inner ring segment 120 3 in view from radially inside. The points in the Figures 3 and 4 The illustrated inner ring segment 120 of an inner ring designed according to the invention has a plurality of indentations 126, which are arranged evenly distributed in particular in the circumferential direction, are made in an inner circumferential surface of inner ring segment 120 and are only indicated in the illustration, with in particular exactly one indentation between two adjacent guide vane receptacles 124 of a pair of guide vane receptacles 124 is arranged.

Durch die erfindungsgemäßen Vertiefungen 126 wird die Querschnittsfläche des Innenringsegments 120, insbesondere eine Wandstärke des Innenringsegments 120, lokal reduziert. Hierdurch kann vorteilhaft ein verbessertes, transientes Aufheizverhalten des Innenringsegments 120 und damit des ganzen Innenrings erreicht werden, da weniger Material des Innenrings aufgeheizt werden muss. Insbesondere kann ein verbessertes, transientes Temperaturprofil in radialer Richtung y erreicht werden, insbesondere ein Temperaturprofil mit einem geringeren Temperaturgradienten in radialer Richtung y.The indentations 126 according to the invention reduce the cross-sectional area of the inner ring segment 120, in particular a wall thickness of the inner ring segment 120, locally. As a result, an improved, transient heating behavior of the inner ring segment 120 and thus of the entire inner ring can advantageously be achieved, since less material of the inner ring has to be heated. In particular, an improved, transient temperature profile can be achieved in the radial direction y, in particular a temperature profile with a lower temperature gradient in the radial direction y.

Erfindungsgemäß weisen die Vertiefungen 126 dabei in axialer Richtung x eine grö-ßere Ausdehnung auf als in Umfangsrichtung. Dadurch ergibt sich ein besonders vorteilhaftes thermisches Verhalten des Innenrings bzw. der Innenringsegmente 120 im Betrieb einer zugehörigen Turbomaschine.According to the invention, the depressions 126 have a greater extent in the axial direction x than in the circumferential direction. This results in a particularly advantageous thermal behavior of the inner ring or the inner ring segments 120 during operation of an associated turbomachine.

Die Vertiefungen 126 weisen bei diesem Ausführungsbeispiel dabei jeweils eine geschlossene Umfangskontur 127 auf, wobei die Umfangskontur im Bereich ihrer axialen Erstreckung 127A und 127B jeweils parallel, d.h. mit konstantem Abstand, zu einer Umfangskontur der Leitschaufelaufnahmen 124 verläuft und in ihrem sich in Umfangsrichtung erstreckenden Abschnitten 127C und 127D jeweils parallel zu einer Umfangskontur des Innenringsegments 120 verläuft.In this exemplary embodiment, the depressions 126 each have a closed peripheral contour 127, with the peripheral contour in the region of its axial extension 127A and 127B running parallel, i.e. at a constant distance, to a peripheral contour of the guide vane receptacles 124 and in its sections 127C extending in the peripheral direction and 127D each runs parallel to a peripheral contour of the inner ring segment 120 .

Die Vertiefungen 126 weisen dabei insbesondere eine im Wesentlichen knochenförmige Umfangskontur 127 auf, bezogen auf eine Projektion in eine Tangentialebene des Innenringsegments 120. Die Vertiefungen 126 sind ferner symmetrisch in axialer Richtung ausgebildet und erstrecken sich insbesondere lokal zwischen zwei angrenzenden, insbesondere benachbarten Leitschaufelaufnahmen 124, nahezu vollständig über den Bereich zwischen diesen Leitschaufelaufnahmen 124.The indentations 126 have in particular a substantially bone-shaped peripheral contour 127, based on a projection into a tangential plane of the inner ring segment 120. The indentations 126 are also embodied symmetrically in the axial direction and extend, in particular locally, almost between two adjacent, in particular adjacent guide vane receptacles 124 completely over the area between these vane mounts 124.

Fig. 5 zeigt einen Ausschnitt eines zweiten Innenringsegments 220 eines zweiten Ausführungsbeispiels eines erfindungsgemäßen Innenrings in perspektivischer Darstellung. Fig. 6 zeigt das Innenringsegment 220 aus Fig. 5 in einer anderen perspektivischen Darstellung, wobei dieses Ausführungsbeispiel eines Innenringsegments 220 eines erfindungsgemäßen Innenrings Teil eines sowohl in Umfangsrichtung als auch in axialer Richtung x geteilten Innenrings ist, wobei eine Teilebene in axialer Richtung dabei mittig durch die Leitschaufelaufnahmen 224 und die Vertiefungen 226 hindurch verläuft. figure 5 shows a section of a second inner ring segment 220 of a second exemplary embodiment of an inner ring according to the invention in a perspective representation. 6 shows the inner ring segment 220 from figure 5 in another perspective view, this embodiment of an inner ring segment 220 of an inner ring according to the invention part of both in the circumferential direction as inner ring which is also divided in the axial direction x, with a partial plane running in the axial direction centrally through the guide vane receptacles 224 and the depressions 226 .

In dieser Darstellung sind die erfindungsgemäßen Vertiefungen 226, welche ebenfalls eine im Wesentlichen knochenförmige, jedoch in diesem Fall nicht näher bezeichnete Umfangskontur aufweisen, besonders gut zu erkennen. Die Vertiefungen 226 weisen jeweils eine Bodenfläche 228 auf, wobei die einzelnen Vertiefungen 228 bei diesem Ausführungsbeispiel über nahezu die gesamte Bodenfläche 228 jeweils eine konstante Tiefe T und damit eine konstante, lokale Wandstärke im Bereich der Vertiefungen 226 aufweisen.In this representation, the depressions 226 according to the invention, which also have an essentially bone-shaped peripheral contour, but which is not specified in this case, can be seen particularly well. The depressions 226 each have a bottom surface 228, the individual depressions 228 in this exemplary embodiment each having a constant depth T over almost the entire bottom surface 228 and thus a constant, local wall thickness in the region of the depressions 226.

Fig. 7 zeigt einen Ausschnitt eines dritten Ausführungsbeispiels eines erfindungsgemäßen Innenrings in perspektivischer Darstellung, wobei bei diesem Ausführungsbeispiel die Vertiefungen 326 aufgrund der größeren Anzahl und insbesondere engeren Anordnung der Leitschaufelaufnahmen 324 sich über eine kleinere Fläche erstrecken, jedoch ansonsten ähnlich wie bei den zuvor beschriebenen Ausführungsbeispielen ausgebildet sind. 7 shows a section of a third exemplary embodiment of an inner ring according to the invention in a perspective view, with the depressions 326 in this exemplary embodiment extending over a smaller area due to the greater number and in particular closer arrangement of the guide vane receptacles 324, but otherwise being configured similarly to the exemplary embodiments described above.

Sämtliche der vorbeschriebenen Ausführungsbeispiele von erfindungsgemäßen Innenringen haben gemein, dass die Vertiefungen 126, 226, 326, bezogen auf einen funktionsgemäßen Einbauzustand der Innenringsegmente 120, 220, 320 bzw. der zugehörigen Innenringe, jeweils auf einer von den Leitschaufeln abgewandten Seite des Innenrings angeordnet sind, insbesondere in einer inneren Mantelfläche des Innenrings. Des Weiteren sind sämtliche Vertiefungen 126, 226, 326 jeweils durch Zerspanen in die Innenringsegmente 120, 220, 320, insbesondere durch Fräsen, eingebracht worden.All of the above-described exemplary embodiments of inner rings according to the invention have in common that the depressions 126, 226, 326, based on a functional installation state of the inner ring segments 120, 220, 320 or the associated inner rings, are each arranged on a side of the inner ring facing away from the guide vanes. in particular in an inner lateral surface of the inner ring. Furthermore, all depressions 126, 226, 326 have been introduced into the inner ring segments 120, 220, 320 by machining, in particular by milling.

Es hat sich herausgestellt, dass mit einer derartigen Ausgestaltung der Vertiefungen 126, 226, 326 ein besonders vorteilhaftes Aufheizverhalten der Innenringsegmente 120, 220, 320 und damit der zugehörigen Innenringe erreichen lässt, insbesondere ein, in Bezug auf den "Cording-Effekt" verbessertes, insbesondere den "Cording-Effekt" reduzierendes, Aufheizverhalten des jeweiligen Innenrings. Infolgedessen entstehen geringere Leckagen, was sich vorteilhaft auf den Wirkungsgrad und den spezifischen Treibstoffverbrauch des Verdichters auswirkt.It has been found that with such a configuration of the depressions 126, 226, 326, a particularly advantageous heating behavior of the inner ring segments 120, 220, 320 and thus the associated inner rings can be achieved, in particular an improved in particular the heating behavior of the respective inner ring that reduces the "cording effect". Consequently there are fewer leaks, which has a beneficial effect on the efficiency and specific fuel consumption of the compressor.

Ferner lässt sich auf diese Weise, nämlich insbesondere durch vorbeschriebene Vertiefungen 126, 226,326, eine um etwa 15% reduzierte Biegesteifigkeit gegenüber einem vergleichbaren Innenring ohne Vertiefungen erreichen, wodurch eine weitere Verbesserung des "Cording-Effekts" erreicht werden kann.Furthermore, in this way, namely in particular by means of the above-described indentations 126, 226, 326, a flexural rigidity which is reduced by approximately 15% can be achieved compared to a comparable inner ring without indentations, as a result of which a further improvement in the “cording effect” can be achieved.

Des Weiteren führen die Vertiefungen 126, 226, 326 zu einer vorteilhaften Gewichtsreduktion der Innenringe und damit auch zu einer Gewichtsreduktion der Turbomaschine.Furthermore, the depressions 126, 226, 326 lead to an advantageous weight reduction of the inner rings and thus also to a weight reduction of the turbomachine.

Es sei darauf hingewiesen, dass es sich bei den exemplarischen Ausführungen lediglich um Beispiele handelt, die den Schutzbereich, die Anwendungen und den Aufbau in keiner Weise einschränken sollen. Vielmehr wird dem Fachmann durch die vorausgehende Beschreibung ein Leitfaden für die Umsetzung von mindestens einer exemplarischen Ausführung gegeben, wobei diverse Änderungen, insbesondere in Hinblick auf die Funktion und Anordnung der beschriebenen Bestandteile, vorgenommen werden können, ohne den Schutzbereich zu verlassen, wie er sich aus den Ansprüchen ergibt.It should be noted that the exemplary implementations are only examples and are not intended to limit the scope, applications, or construction in any way. Rather, the above description gives the person skilled in the art a guideline for the implementation of at least one exemplary embodiment, with various changes, in particular with regard to the function and arrangement of the components described, being able to be made without departing from the scope of protection as it emerges from the claims.

BezugszeichenlisteReference List

11
Leitschaufelkranzsegment aus dem Stand der TechnikPrior art vane ring segment
1010
Leitschaufelvane
1111
Befestigungszapfen der LeitschaufelGuide vane mounting studs
2020
Innenringsegment aus dem Stand der TechnikState-of-the-art inner ring segment
2121
Dichtungsträgerseal carrier
2222
Dichtstruktursealing structure
2323
Verbindungszapfenconnecting pin
24, 124, 224, 32424, 124, 224, 324
Leitschaufelaufnahmevane mount
2525
Aufnahmebuchsereceiving socket
3030
Rotorrotor
120, 220, 320120, 220, 320
Innenringsegment eines erfindungsgemäßen InnenringsInner ring segment of an inner ring according to the invention
126, 226, 326126, 226, 326
Vertiefungdeepening
127127
Umfangskontur der VertiefungCircumferential contour of the indentation
127A, 127B127A, 127B
Umfangskontur der Vertiefung parallel zu einer Umfangskontur einer benachbarten LeitschaufelaufnahmeCircumferential contour of the recess parallel to a peripheral contour of an adjacent vane mount
127C, 127D127C, 127D
Umfangskontur der Vertiefung parallel zu einer Umfangskontur des InnenringsCircumferential contour of the recess parallel to a peripheral contour of the inner ring
228228
Bodenfläche der Vertiefungbottom surface of the recess
LL
Drehachse der LeitschaufelAxis of rotation of the vane
TT
Tiefe der Vertiefungdepth of recess
xx
axiale Richtungaxial direction
yy
radiale Richtungradial direction

Claims (14)

  1. Inner ring (120, 220, 320) for a guide vane ring for fastening to, in particular adjustable, guide vanes (10) of a turbomachine, in particular of a compressor stage or turbine stage of a gas turbine,
    the inner ring (120, 220, 320) comprising a plurality of guide vane receptacles (124, 224, 324) which are each arranged spaced from each other in the circumferential direction and are in each case designed for receiving a fastening element (11) of a guide vane (10),
    the inner ring (120, 220, 320) comprising, between at least two adjacent guide vane receptacles (124, 224, 324), at least one recess (126, 226, 326) having a wall thickness that is reduced in the radial direction (y) in comparison to a region which adjoins the recess (126, 226, 326) and is outside the recess (126, 226, 326),
    the recess (126, 226, 326) comprising, in relation to an axis of rotation of the turbomachine in a functionally installed state of the inner ring (120, 220, 320) in a turbomachine, a greater extension in the axial direction (x) than in the circumferential direction
    characterized in
    that at least one recess (126, 226, 326) comprises an hourglass-shaped or hourglass-like shaped peripheral contour (127), in particular in relation to a projection of the peripheral contour (127) of the recess (126, 226, 326) in a tangential plane of the inner ring.
  2. Inner ring (120, 220, 320) according to claim 1, characterized in that the inner ring (120, 220, 320) comprises a plurality of recesses (126, 226, 326), in particular a plurality of recesses (126, 226, 326) which are each arranged on a face of the inner ring (120, 220, 320) facing away from the guide vanes, the recesses (126, 226, 326) being arranged, in particular at least substantially equidistantly, distributed over the circumference of the inner ring (120, 220, 320).
  3. Inner ring (120, 220, 320) according to either claim 1 or claim 2, characterized in that exactly one recess (126, 226, 326) is provided at least between two adjacent guide vane receptacles (124, 224, 324) or adjacent groups of guide vane receptacles (124, 224, 324).
  4. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that at least one recess (126, 226, 326), in relation to a functionally installed state of the inner ring (120, 220, 320) in a turbomachine, is arranged on a face of the inner ring (120, 220, 320) facing away from the guide vanes (10), in particular in an inner surface of the inner ring (120, 220, 320) in the radial direction (y), in particular in an inner lateral surface of the inner ring (120, 220, 320).
  5. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that the guide vane receptacles (124, 224, 324) are designed as recesses and the fastening elements (11) are designed as fastening pins (11), the peripheral contour (127) of at least one recess (126, 226, 326) extending at least partially in parallel with a peripheral contour of an adjacent recess (126, 226, 326), in particular in a region (127A, 127B) of the peripheral contour (127) extending substantially in the axial direction (x) of the inner ring, in relation to a functionally installed state in a turbomachine, the peripheral contour (127) extending in particular at least partially in parallel with the peripheral contours of the two adjacent recesses.
  6. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that the peripheral contour (127) of at least one recess (126, 226, 326) extends at least partially in parallel with a contour of the inner ring (120, 220, 320) in the circumferential direction of the inner ring (120, 220, 320), in particular in a region (127C, 127D) of the peripheral contour (127) extending substantially in the circumferential direction of the inner ring (120, 220, 320), in relation to a functionally installed state in a turbomachine.
  7. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that at least one recess (126, 226, 326) comprises a peripheral contour (127) which is completely closed, or open at at least one axial end, in particular at only one axial end.
  8. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that at least one recess (126, 226, 326) comprises a bottom surface (228), in particular at least in the region of the bottom surface (228), the recess (126, 226, 326) having at least partially, in particular over the entire bottom surface (228), a constant depth (T).
  9. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that the inner ring (120, 220, 320) is formed in one or more parts.
  10. Inner ring (120, 220, 320) according to any of the preceding claims, characterized in that at least one recess (126, 226, 326) has been introduced into the inner ring (120, 220, 320) by a separating production method.
  11. Guide vane ring for a turbomachine, in particular a compressor stage or turbine stage of a gas turbine, comprising an inner ring (120, 220, 320) and, in particular adjustable, guide vanes (10) on which the inner ring (120, 220, 320) is fastened, characterized in that the inner ring (120, 220, 320) is designed according to any of claims 1 to 10.
  12. Guide vane ring according to claim 11, characterized in that the guide vane ring comprises a seal carrier or a seal carrier segment (21), the seal carrier or the seal carrier segment (21) being arranged on the inner ring (120, 220, 320) on the face facing away from the guide vanes (10) and at least one recess (126, 226, 326) arranged in a surface facing away from guide vanes (10) being at least partially, in particular completely, covered.
  13. Turbomachine, in particular gas turbine, comprising at least one compressor stage or turbine stage having an inner ring (120, 220, 320), characterized in that the inner ring (120, 220, 320) is designed according to any of claims 1 to 10.
  14. Method for producing an inner ring (120, 220, 320), which is designed according to any of claims 1 to 10, characterized in that at least one recess (126, 226, 326) is produced by means of a separating production method, in particular by means of mechanical processing, in particular by machining, in particular by machining with geometrically defined cutting edges, in particular by milling.
EP19160760.5A 2018-03-07 2019-03-05 Inner ring for a turbomachine and method for producing said inner ring Active EP3536913B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018203442.7A DE102018203442A1 (en) 2018-03-07 2018-03-07 Inner ring for a turbomachine, vane ring with an inner ring, turbomachinery and method of making an inner ring

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EP3536913A1 EP3536913A1 (en) 2019-09-11
EP3536913B1 true EP3536913B1 (en) 2023-02-15

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DE102021129033A1 (en) 2021-11-08 2023-05-11 MTU Aero Engines AG Adjustable guide vane with a convex, radially inner bearing section for a gas turbine, in particular an aircraft gas turbine

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FR2723614B1 (en) * 1994-08-10 1996-09-13 Snecma DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES.
FR2751694B1 (en) 1996-07-25 1998-09-04 Snecma ARRANGEMENT AND METHOD FOR ADJUSTING THE STATOR RING DIAMETER
DE10161292A1 (en) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Bearing ring for the storage of blade roots of adjustable stator blades in the high pressure compressor of a gas turbine
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
FR2953487B1 (en) 2009-12-07 2011-11-18 Snecma PROPELLER HUB WITH REINFORCED POLYGON RING AND TURBOMACHINE EQUIPPED WITH SUCH HUB.
DE102012220249B4 (en) * 2012-11-07 2017-08-17 MTU Aero Engines AG Guide vane, turbomachine and inner ring
US20140140822A1 (en) * 2012-11-16 2014-05-22 General Electric Company Contoured Stator Shroud
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DE102016215784A1 (en) * 2016-08-23 2018-03-01 MTU Aero Engines AG Positioning element with recesses for a guide vane assembly

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EP3536913A1 (en) 2019-09-11
US11098603B2 (en) 2021-08-24
DE102018203442A1 (en) 2019-09-12

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