EP3536913B1 - Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure - Google Patents

Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure 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.)
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Application number
EP19160760.5A
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German (de)
English (en)
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EP3536913A1 (fr
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/fr
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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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (14)

  1. Bague intérieure (120, 220, 320) pour une couronne d'aube directrice destinée à être fixée sur des aubes directrices (10), en particulier réglables, d'une turbomachine, en particulier d'un étage de compresseur ou de turbine d'une turbine à gaz,
    dans laquelle la bague intérieure (120, 220, 320) présente plusieurs logements d'aube directrice (124, 224, 324) respectivement espacés les uns des autres dans la direction circonférentielle et respectivement réalisés pour la réception d'un élément de fixation (11) d'une aube directrice (10),
    dans laquelle la bague intérieure (120, 220, 320) présente au moins une cavité (126, 226, 326) entre au moins deux logements d'aube directrice (124, 224, 324) adjacents, laquelle cavité comportant une épaisseur de paroi réduite dans la direction radiale (y) par rapport à une région adjacente à la cavité (126, 226, 326) à l'extérieur de la cavité (126, 226, 326),
    dans laquelle la cavité (126, 226, 326) présente une plus grande expansion dans la direction axiale (x) que dans la direction circonférentielle par rapport à un axe de rotation de la turbomachine dans un état de montage fonctionnel de la bague intérieure (120, 220, 320) dans une turbomachine
    caractérisée en ce
    qu'au moins une cavité (126, 226, 326) présente un contour circonférentiel (127) en forme de sablier ou à la manière d'un sablier, en particulier par rapport à une projection du contour circonférentiel (127) de la cavité (126, 226, 326) dans un plan tangentiel de la bague intérieure.
  2. Bague intérieure (120, 220, 320) selon la revendication 1,
    caractérisée en ce que la bague intérieure (120, 220, 320) présente plusieurs cavités (126, 226, 326), en particulier plusieurs cavités (126, 226, 326) disposées respectivement sur un côté de la bague intérieure (120, 220, 320) opposé aux aubes directrices, les cavités (126, 226, 326) étant réparties sur la circonférence de la bague intérieure (120, 220, 320), en particulier au moins de manière sensiblement équidistante.
  3. Bague intérieure (120, 220, 320) selon la revendication 1 ou 2,
    caractérisée en ce qu'exactement une cavité (126, 226, 326) est prévue au moins entre deux logements d'aube directrice (124, 224, 324) adjacents ou des groupes adjacents de logements d'aube directrice (124, 224, 324).
  4. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce qu'au moins une cavité (126, 226, 326) est disposée sur un côté de la bague intérieure (120, 220, 320) opposé aux aubes directrices (10) par rapport à un état de montage fonctionnel de la bague intérieure (120, 220, 320) dans une turbomachine, en particulier dans une surface de la bague intérieure (120, 220, 320) située à l'intérieur dans la direction radiale (y), en particulier dans une surface d'enveloppe intérieure de la bague intérieure (120, 220, 320).
  5. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce que les logements d'aube directrice (124, 224, 324) sont réalisés sous forme d'évidements et les éléments de fixation (11) sont réalisés sous forme de tourillons de fixation (11), le contour circonférentiel (127) d'au moins une cavité (126, 226, 326) s'étendant au moins partiellement parallèlement à un contour circonférentiel d'un évidement (126, 226, 326) adjacent, en particulier dans une zone (127A, 127B) du contour circonférentiel (127) s'étendant sensiblement dans la direction axiale (x) de la bague intérieure, par rapport à un état de montage fonctionnel dans une turbomachine, le contour circonférentiel (127) s'étendant en particulier au moins partiellement parallèlement aux contours circonférentiels de deux évidements voisins.
  6. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce que le contour circonférentiel (127) d'au moins une cavité (126, 226, 326) s'étend au moins partiellement parallèlement à un contour de la bague intérieure (120, 220, 320) dans la direction circonférentielle de la bague intérieure (120, 220, 320), en particulier dans une zone (127C, 127D) du contour circonférentiel (127) s'étendant sensiblement dans la direction circonférentielle de la bague intérieure (120, 220, 320), par rapport à un état de montage fonctionnel dans une turbomachine.
  7. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce qu'au moins une cavité (126, 226, 326) présente un contour circonférentiel (127) complètement fermé ou ouvert au niveau d'au moins une extrémité axiale, en particulier au niveau d'une seule extrémité axiale.
  8. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce qu'au moins une cavité (126, 226, 326) présente une surface de fond (228), la cavité (126, 226, 326) présentant une profondeur (T) constante, en particulier au moins partiellement au moins dans la zone de la surface de fond (228), en particulier sur toute la surface de fond (228).
  9. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce que la bague intérieure (120, 220, 320) est réalisée en une ou plusieurs pièces.
  10. Bague intérieure (120, 220, 320) selon l'une des revendications précédentes, caractérisée en ce qu'au moins une cavité (126, 226, 326) a été introduite dans la bague intérieure (120, 220, 320) par un procédé de fabrication séparé.
  11. Couronne d'aube directrice pour une turbomachine, en particulier un étage de compresseur ou de turbine d'une turbine à gaz, comportant une bague intérieure (120, 220, 320) et des aubes directrices (10), en particulier réglables, auxquelles est fixée la bague intérieure (120, 220, 320), caractérisée en ce que la bague intérieure (120, 220, 320) est réalisée selon l'une des revendications 1 à 10.
  12. Couronne d'aube directrice selon la revendication 11,
    caractérisée en ce que la couronne d'aube directrice présente un support d'étanchéité ou un segment de support d'étanchéité (21), le support d'étanchéité ou le segment de support d'étanchéité (21) étant disposé sur la bague intérieure (120, 220, 320) sur le côté opposé aux aubes directrices (10) et recouvrant au moins partiellement, en particulier complètement, au moins une cavité (126, 226, 326) disposée dans une surface opposée aux aubes directrices (10).
  13. Turbomachine, en particulier turbine à gaz, comportant au moins un étage de compresseur ou de turbine comportant une bague intérieure (120, 220, 320), caractérisée en ce que la bague intérieure (120, 220, 320) est réalisée selon l'une des revendications 1 à 10.
  14. Procédé de production d'une bague intérieure (120, 220, 320) réalisée selon l'une des revendications 1 à 10, caractérisé en ce qu'au moins une cavité (126, 226, 326) est produite par un procédé de fabrication séparé, en particulier par un usinage mécanique, en particulier par enlèvement de copeaux, en particulier par enlèvement de copeaux à arête définie géométriquement, en particulier par fraisage.
EP19160760.5A 2018-03-07 2019-03-05 Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure Active EP3536913B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018203442.7A DE102018203442A1 (de) 2018-03-07 2018-03-07 Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings

Publications (2)

Publication Number Publication Date
EP3536913A1 EP3536913A1 (fr) 2019-09-11
EP3536913B1 true EP3536913B1 (fr) 2023-02-15

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US (1) US11098603B2 (fr)
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021129033A1 (de) 2021-11-08 2023-05-11 MTU Aero Engines AG Verstellleitschaufel mit konvex ausgeführtem, radial innerem Lagerabschnitt für eine Gasturbine, insbesondere Fluggasturbine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
FR2751694B1 (fr) 1996-07-25 1998-09-04 Snecma Agencement et procede de reglage de diametre d'anneau de stator
DE10161292A1 (de) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
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 (fr) 2009-12-07 2011-11-18 Snecma Moyeu d'helice a anneau polygonal renforce et turbomachine equipee d'un tel moyeu.
DE102012220249B4 (de) * 2012-11-07 2017-08-17 MTU Aero Engines AG Leitschaufelkranz, Strömungsmaschine und Innenring
US20140140822A1 (en) * 2012-11-16 2014-05-22 General Electric Company Contoured Stator Shroud
EP2835499B1 (fr) * 2013-08-06 2019-10-09 MTU Aero Engines GmbH Grille d'aubes et turbomachine associée
WO2015031058A1 (fr) * 2013-08-28 2015-03-05 United Technologies Corporation Douille d'aube variable
WO2015050676A1 (fr) * 2013-10-02 2015-04-09 Siemens Aktiengesellschaft Ensemble joint comprenant des rainures dans un côté faisant face à l'arrière d'une plateforme dans une turbine à gaz
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
US9533485B2 (en) * 2014-03-28 2017-01-03 Pratt & Whitney Canada Corp. Compressor variable vane assembly
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP3176385B1 (fr) * 2015-12-04 2022-01-26 MTU Aero Engines AG Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator
EP3176384B1 (fr) * 2015-12-04 2023-07-12 MTU Aero Engines AG Virole interne, secteur de virole interne, aubage statorique et turbomachine
DE102016215784A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Positionierungselement mit Aussparungen für eine Leitschaufelanordnung

Also Published As

Publication number Publication date
US20190277148A1 (en) 2019-09-12
US11098603B2 (en) 2021-08-24
DE102018203442A1 (de) 2019-09-12
EP3536913A1 (fr) 2019-09-11

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