EP3536913A1 - 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
EP3536913A1
EP3536913A1 EP19160760.5A EP19160760A EP3536913A1 EP 3536913 A1 EP3536913 A1 EP 3536913A1 EP 19160760 A EP19160760 A EP 19160760A EP 3536913 A1 EP3536913 A1 EP 3536913A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
recess
turbomachine
vane
ring
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.)
Granted
Application number
EP19160760.5A
Other languages
German (de)
English (en)
Other versions
EP3536913B1 (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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3536913A1 publication Critical patent/EP3536913A1/fr
Application granted granted Critical
Publication of EP3536913B1 publication Critical patent/EP3536913B1/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
    • 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
    • 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
    • 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 gas turbine, with such an inner ring and a method for its production.
  • the inner rings are usually exposed to thermal stresses, in particular partially changing and / or high temperature gradients, in particular by the vane ring flowing through and thus the inner ring at least partially flowing around the working fluid and / or by sliding seals between the vane ring and a rotor rotating relative thereto.
  • thermal stress can lead to undesirable thermally induced deformation of the inner ring, in particular for widening of gaps and consequently undesirable leakage, which can adversely affect the efficiency of the turbomachine.
  • Generic inner rings are basically known from the prior art, for example from the FR 2 953 487 , where the FR 2 953 487 the use of a polygonal inner ring teaches which, relative to the inner ring in a functional installation state in a turbomachine, between the receptacles for the guide vanes in the radially outward and circumferentially extending reinforcing elements, in particular reinforcing ribs having.
  • An object of one embodiment of the present invention is to provide an improved inner ring.
  • an inner ring having the features of claim 1, by a vane ring according to claim 12, by a turbomachine according to claim 14, each having (at least) an inner ring described herein, and a method of manufacturing an inner ring described herein according to claim 15 solved.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • 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 plurality of circumferentially spaced-apart guide vane receptacles, in particular recesses, each for receiving a Fastening element, in particular a fastening pin, a guide vane are formed.
  • the inner ring has at least one recess with a wall thickness reduced in the radial direction in relation to an area adjoining the recess outside the recess.
  • the recess in particular the at least one recess, with respect to an axis of rotation of a turbomachine in a functional installation state of the inner ring in a turbomachine, in the axial direction a greater extent than in the circumferential direction.
  • the directional indication "axial” in the present case refers in a usual way to a direction parallel to the rotation or (main) machine axis of the turbomachine, the direction indication “circumferential direction” corresponding to a rotation direction about this rotation or (main) machine axis, the direction indication " radially “in a direction perpendicular to the axial and circumferential directions.
  • the direction “tangential” refers accordingly to a direction which is perpendicular to the axial direction and the radial direction, wherein in particular all directions are an inner ring according to the invention and / or a guide vane according to the invention, each related to a functional installation state in a turbomachine.
  • Guide blade 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 supported.
  • a “depression” in the sense of the present invention is understood in particular to mean a local notch 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 in the inner ring by means of one or more such depressions.
  • thermally induced movement and / or deformation of the inner ring during operation can be influenced, in particular reduced, by the depression (s), and in particular a change in its shape, in particular its diameter and / or roundness, can be influenced, in particular reduced.
  • a sealing effect between guide vanes and inner ring in the area of the vane receptacles and / or between the vane ring and the rotor and / or an inlet can be reduced and thus the operating behavior of a turbomachine, in particular an efficiency, can be improved.
  • the so-called undesired “cording effect” can be reduced by means of one or more such depressions.
  • 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 of the inner ring, which can occur particularly at split inner rings at the dividing planes and which in particular by a transient, radial Temperature profile due to the different heating times of the inner ring on the side of the vanes, which directly from the working fluid and thus heated quickly, and the side facing away from the vanes, slowly heating up side, arise.
  • 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 configuration of the recess, locally reduced.
  • an improved, transient heating behavior of the inner ring can 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, whereby, in particular with a suitable embodiment of the recess (s), a, in relation to the "Cording effect "improved, in particular the” Cording effect "reducing, heating behavior of the inner ring can be achieved.
  • undesirable widening of gaps, in particular ovalization of the vane receptacles, and / or leakage of sealing fins into the sealing structure of a seal carrier may be reduced or even avoided, thereby reducing leakage and, as a result, efficiency improved turbomachine and / or reduced specific fuel consumption and / or in the case of a designed as a compressor turbomachine a surge limit can be increased.
  • a “pumping limit” is understood to mean a stable volume flow which is at least required to achieve a desired compression ratio, with higher compression generally being possible with increasing volume flow.
  • a weight reduction of the inner ring and thus of a vane ring and of a turbomachine can be achieved by the recess (s) according to the invention.
  • the inner ring is in particular designed such, in particular the recesses of the inner ring, that the inner ring with respect to an inner ring without recesses by at least 10%, in particular by at least or reduced by about 15% flexural rigidity, in particular in the circumferential direction.
  • the inner ring in particular has a plurality of depressions, in particular a plurality of depressions, each arranged on a side of the inner ring facing away from the guide vanes, wherein the Recesses, in particular at least substantially equidistant, are distributed over the circumference of the inner ring.
  • the inner ring has exactly one recess in particular between at least one pair of adjacent pairs of vane seats or a pair of adjacent sets of vane seats, in particular exactly one recess between each two vane seats or two sets of vane seats.
  • a particularly advantageous heating behavior and / or an advantageous reduction of the bending stiffness 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 uniform (re) bending stiffness of the inner ring circumferential direction.
  • At least one depression relative to 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 radially inner surface of the inner ring, in particular in an inner circumferential surface of the inner ring.
  • a faster heating of the inner side of the inner ring and consequently a particularly advantageous temperature distribution in the radial direction with regard to the "cording effect" can be achieved, in particular a faster heating of the side of the inner ring facing away from the guide vanes, based on a functional installation state in a turbomachine.
  • the inner ring can also be introduced into at least one surface of the inner ring facing the guide vanes.
  • the circumferential contour of at least one recess runs in particular at least partially parallel to a circumferential contour of an adjacent recess, in particular in a region of the circumferential contour extending essentially in the axial direction of the inner ring, with respect to a functional installation state in a turbomachine, wherein the Peripheral contour runs in particular at least partially parallel to the circumferential contours of both adjacent recesses.
  • the recesses and the recesses delimitation webs, in particular, preferably at least partially, along its longitudinal extent may have a constant thickness.
  • the circumferential contour of at least one recess runs in particular at least partially parallel to a contour of the inner ring in the circumferential direction of the inner ring, in particular in a region of the circumferential contour extending substantially in the circumferential direction of the inner ring, relative to a functional installation state in a turbomachine. In this way, a particularly advantageous thermal behavior of the inner ring can be achieved.
  • At least one depression has a bone-shaped, bone-shaped, hourglass-shaped or hourglass-shaped peripheral contour, in particular with respect to a projection of the circumferential contour of the depression into a tangential plane of the inner ring.
  • the circumferential contour is in particular symmetrical or asymmetrical in and / or formed to an axial direction.
  • a "tangential plane” is understood to mean a plane perpendicular to the radial direction, in particular a plane extending perpendicularly to an associated radius.
  • At least one recess has a completely closed or at least one axial end, in particular only at one axial end, open peripheral contour.
  • a depression with an open peripheral contour at its axial ends can be produced particularly easily, in particular by machining.
  • a recess with a fully closed peripheral contour usually results in less leakage than a comparable recess with an open at one axial peripheral contour, especially since the closed at the axial ends peripheral contour a flow of the working fluid from the vane side through the open end in the Reduces depression on the side facing away from the vanes side of the inner ring or prevented.
  • At least one recess has a bottom surface, wherein the recess has a constant depth at least partially, in particular over the entire bottom surface, in particular such that the inner ring in the region of the bottom surface in particular a has constant wall thickness and / or an inner contour with a constant radius relative to the (main) machine axis or the axis of rotation of the turbomachine relative to a functional installation state of the inner ring in a turbomachine.
  • This can be especially simple way an effective wall thickness reduction can be achieved, especially with simultaneous advantageous thermal behavior of the inner ring.
  • the depth of at least one depression is chosen to be as large as possible and as a result the wall thickness is minimized, in particular locally in the region of the depression and / or in an area adjacent to the depression.
  • the inner ring is formed in one piece. In another embodiment of the present invention, the inner ring is designed in several parts, in particular in the circumferential direction and / or split in the axial direction.
  • the inner ring is divided in an embodiment of the present invention in the circumferential direction, it has in particular a plurality of inner ring segments and in particular composed of a plurality of inner ring segments, in particular of at least two inner ring segments, which in this case preferably each have a circumferential angle of about, in particular exactly, 180 ° or from three inner ring segments, which preferably each extend over a circumferential angle of about, in particular, exactly 120 °.
  • in each case in particular two circumferentially adjacent inner ring segments are coupled to each other at their abutment surfaces, in particular by means of at least one, extending in the circumferential direction of the connecting pin or pin, in particular connected.
  • the inner ring or at least one inner ring segment may be divided in the axial direction, wherein the pitch extends in the circumferential direction in particular over the entire length of the inner ring or the inner ring segment and in particular in a common radial plane through the inner ring or the associated inner ring segment runs.
  • the individual inner ring parts with the help of at least one, in axial Direction extending connecting pin - or pin coupled together, in particular connected.
  • At least one depression in particular all depressions, has been introduced into 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.
  • 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 wells can be particularly easily introduced into the inner ring.
  • particularly simple and precise recesses can be introduced in this way.
  • An inventive vane ring for a turbomachine in particular a compressor or turbine stage of a gas turbine with an inner ring and, in particular adjustable guide vanes, on which the inner ring is fixed, has an inner ring formed according to the present invention.
  • At least one guide vane is connected to the inner ring by means of a fastening pin extending in the radial direction, which is inserted into a correspondingly formed guide vane receptacle of the inner ring, in particular supported in the radial direction on the inner ring, in particular rotatable about a longitudinal axis in the inner ring stored.
  • a receiving bushing is further provided between the inner ring and the fastening pin.
  • the guide vane ring additionally has, in particular, a seal carrier or a seal carrier segment, wherein the seal carrier or the seal carrier segment is arranged in particular on the side facing away from the guide vanes and, in particular at least partially, a depression arranged in a surface facing away from the guide vanes, especially completely, covering.
  • a turbomachine according to the invention in particular gas turbine, with at least one compressor or turbine stage with an inner ring has an inner ring formed according to the present invention.
  • a turbomachine in particular has one or more compressor and / or turbine stages.
  • one or more of these compressor and turbine stages each have a rotor and a guide grid, wherein in particular one or more of these guide bars have a guide blade 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 inventive inner ring is produced in one embodiment of a method according to the present invention by at least one recess of the inner ring, in particular all wells, is produced by a separating manufacturing process, in particular by a mechanical processing, in particular by machining, in particular by machining with a geometrically defined cutting edge , in particular by milling.
  • Fig. 1 shows for better understanding of the invention, a detail of a generic, known from the prior art vane ring segment 1 designed as a compressor, known from the prior art turbomachine with an inner ring segment 20 in the region of the inner ring segment 20 in side view.
  • the inner ring segment 20 is fastened to the guide vanes 10 in a manner known from the prior art, wherein the inner ring segment 20 has guide vane housings 24 distributed uniformly in the circumferential direction, in particular as through-openings, wherein the vanes 10 have fastening pins extending in the radial direction y 11 are connected to the inner ring segment 20 and are supported in the radial direction on the inner ring segment 20.
  • the guide vanes 10 are adjustable and rotatably connected about a longitudinal axis L with the inner ring segment 20.
  • a bushing 25 is in each case introduced into the passage opening for the guide blade receptacle 24.
  • the vane ring 1 further comprises a on a side facing away from the vanes 10 on the inner ring segment 20 fastened seal carrier segment 21, wherein the seal carrier segment 21 is also arranged in a known manner on the inner ring segment 20, in which case , in particular in favor of a high sealing effect, which are formed as passage openings formed Leitschaufelingn 24 on a side facing away from the vanes 10 side of the inner ring by the seal carrier segment 21.
  • 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 cooperates with so-called sealing fins 31, which are fastened to the rotor and extend radially outward from the rotor, and have a gap between them the housing fixedly arranged vane ring or vane ring segment 1 and the rotatably mounted rotor 30 of the turbomachine seals to reduce flow losses due to leakage during flow around the guide vanes 10, in particular a reduction in the volume flow in the guide vanes 10.
  • the vane ring segment 1 is part of a vane ring, which is divided in the circumferential direction into a plurality of vane ring segments 1, each vane ring segment 1 having an inner ring segment 20 and a corresponding seal carrier segment 21.
  • each inner ring segment 20 at one of its end faces in the circumferential direction a connecting pin 23 and at the other end side not shown here, corresponding to the connecting pin 23 corresponding formed recess.
  • Fig. 2 shows a section of the vane ring segment Fig. 1 in a perspective view, wherein in this illustration, in particular, the connecting pin 23 on the end face of the inner ring segment 20, as a through-openings trained guide blade receptacles 24 and arranged in the through holes for the guide blade receptacles 24 sockets 25 can be seen.
  • the guide vanes 10 are flowed around in the axial direction x by a working fluid, as a result of which the inner ring or the individual inner ring segments 20 heat up, whereby the inner ring segments 20 heat up faster on their outer side due to the working fluid flowing directly past them than on their facing away from the guide vanes 10 and the seal carrier segment 21 facing inside, which can lead to the widening of gaps, in particular for widening of sealing gaps and consequently leaks.
  • Fig. 3 shows a section of a first embodiment of an inner ring segment 120 of a multi-part, divided in the circumferential direction, inner ring according to the invention in a perspective view in view of radially inward and Fig. 4 the inner ring segment 120 from Fig. 3 in view of radially inward.
  • This points in the 3 and 4 illustrated inner ring segment 120 of an inventively designed inner ring several, in particular distributed uniformly in the circumferential direction, introduced into an inner circumferential surface of the inner ring segment 120, only indicated in the representation depressions 126, in particular in each case exactly one depression between two adjacent Leitschaufelabilityn 124 of a pair of Leitschaufelagen 124th is arranged.
  • the cross-sectional area of the inner ring segment 120 in particular a wall thickness of the inner ring segment 120, locally reduced.
  • an improved, transient heating behavior of the inner ring segment 120 and thus of the entire inner ring can be achieved, since less material of the inner ring has to be heated.
  • an improved, transient temperature profile in the radial direction y can be achieved, 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 inner ring segments 120 during operation of an associated turbomachine.
  • the recesses 126 in this embodiment each have a closed circumferential contour 127, wherein the circumferential contour in the region of their axial extent 127A and 127B each parallel, i. at a constant pitch, to a circumferential contour of the vane receivers 124 and extends in their circumferentially extending portions 127C and 127D each parallel to a circumferential contour of the inner ring segment 120.
  • the recesses 126 in this case have, in particular, a substantially bone-shaped circumferential contour 127, based on a projection into a tangential plane of the inner ring segment 120.
  • the recesses 126 are also formed symmetrically in the axial direction and extend in particular locally between two adjoining, in particular adjacent, guide blade receptacles 124 completely over the area between these vane mounts 124.
  • Fig. 5 shows a section of a second inner ring segment 220 of a second embodiment of an inner ring according to the invention in a perspective view.
  • Fig. 6 shows the inner ring segment 220 Fig. 5 in another perspective view, this embodiment of an inner ring segment 220 of an inner ring according to the invention is part of an inner ring divided both in the circumferential direction and in the axial direction x, wherein a part plane in the axial direction thereby passes centrally through the Leitschaufelingn 224 and the recesses 226 therethrough.
  • the depressions 226 which likewise have a substantially bone-shaped but in this case unspecified circumferential contour, can be recognized particularly well.
  • the recesses 226 each have a bottom surface 228, wherein the individual recesses 228 in this embodiment over almost the entire bottom surface 228 respectively a constant depth T and thus have a constant, local wall thickness in the region of the recesses 226.
  • Fig. 7 shows a section of a third embodiment of an inner ring according to the invention in a perspective view, in this embodiment, the recesses 326 extend over a smaller area due to the larger number and in particular narrower arrangement of the Leitschaufelagen 324, but otherwise similar to the embodiments described above.
  • All of the above-described embodiments of inner rings according to the invention have in common that the recesses 126, 226, 326, based on a functional installation state of the inner ring segments 120, 220, 320 and the associated inner rings, respectively arranged on a side facing away from the vanes side of the inner ring, in particular in an inner circumferential surface of the inner ring. Furthermore, all recesses 126, 226, 326 have been introduced by machining into the inner ring segments 120, 220, 320, in particular by milling.
  • the recesses 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)
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 true EP3536913A1 (fr) 2019-09-11
EP3536913B1 EP3536913B1 (fr) 2023-02-15

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EP19160760.5A Active EP3536913B1 (fr) 2018-03-07 2019-03-05 Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure

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US (1) US11098603B2 (fr)
EP (1) EP3536913B1 (fr)
DE (1) DE102018203442A1 (fr)

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DE102021129033A1 (de) 2021-11-08 2023-05-11 MTU Aero Engines AG Verstellleitschaufel mit konvex ausgeführtem, radial innerem Lagerabschnitt für eine Gasturbine, insbesondere Fluggasturbine

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EP3536913B1 (fr) 2023-02-15
US11098603B2 (en) 2021-08-24
US20190277148A1 (en) 2019-09-12
DE102018203442A1 (de) 2019-09-12

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