EP3176386A1 - Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés - Google Patents

Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés Download PDF

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Publication number
EP3176386A1
EP3176386A1 EP15198116.4A EP15198116A EP3176386A1 EP 3176386 A1 EP3176386 A1 EP 3176386A1 EP 15198116 A EP15198116 A EP 15198116A EP 3176386 A1 EP3176386 A1 EP 3176386A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
ring
intermediate housing
ring system
segment
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
EP15198116.4A
Other languages
German (de)
English (en)
Other versions
EP3176386B1 (fr
Inventor
Vitalis Mairhanser
Werner Humhauser
Lothar Albers
Georg Zotz
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
Original Assignee
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
Priority to EP15198116.4A priority Critical patent/EP3176386B1/fr
Priority to US15/363,914 priority patent/US10494942B2/en
Publication of EP3176386A1 publication Critical patent/EP3176386A1/fr
Application granted granted Critical
Publication of EP3176386B1 publication Critical patent/EP3176386B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an inner ring system for a strictlysleitschaufelkranz a turbomachine.
  • the invention further relates to an inner ring and an intermediate housing for such an inner ring system and a turbomachine with such an inner ring system.
  • an inner ring or bearing ring for a vane ring of a turbomachine is known.
  • the inner ring is axially divided into a first and a second ring segment, which in the assembled state together form recesses for the storage of blade roots of the vanes of the guide vane ring.
  • the inner ring has for this purpose a plurality of axial mounting holes or openings, via which the two ring segments are screwed together.
  • the assembly of the inner ring takes place in a second stage of a compressor of the turbomachine, so that the inner ring is supported by the vane ring.
  • a disadvantage of the known inner ring is the fact that this has a comparatively low mechanical stability in the assembled state in a turbomachine and can absorb loads occurring only very limited.
  • the inner ring is thus not suitable for an inlet guide vane ring, that is to say for a first stage of a compressor or a turbine.
  • compressor or turbine in particular, a compressor module or a turbine module of the turbomachine is meant. Under certain circumstances, particularly high loads may occur here, for example due to bird strikes.
  • a compressor module may be, for example, a low-pressure compressor, medium-pressure compressor or high-pressure compressor.
  • Object of the present invention is to provide an inner ring system for a first stage of a compressor or a turbine, which allows improved aerodynamic properties and a reduction in maintenance costs.
  • Other objects of the invention are to provide an inner ring and an intermediate housing for such an inner ring system and a turbomachine with such an inner ring system.
  • a first aspect of the invention relates to an inner ring system for an inlet guide ring of a turbomachine.
  • the inner ring system comprises an intermediate housing for receiving structural loads and an inner ring, which is divided axially into a first and a second ring segment, which together form recesses for supporting radially inner end portions of vanes of strictlysleitschaufelkranzes, wherein at least the second ring segment by means of screws on the intermediate housing is fixed.
  • the inner ring system has a particularly high mechanical stability, since occurring during operation of an associated turbomachine loads that are transmitted through the guide vanes mounted in the recesses on the ring segments of the inner ring, can be forwarded to the intermediate housing, which as a machine-fixed element, the structural loads absorb and distribute much better than is possible with inner rings which are supported exclusively by a vane ring.
  • the intermediate housing which as a machine-fixed element
  • the structural loads absorb and distribute much better than is possible with inner rings which are supported exclusively by a vane ring.
  • the more accurate positioning of the vanes, which is less warped, also reduces the wear in the area of the vanes, which results in a corresponding reduction in maintenance costs.
  • the screwing of the inner ring to the intermediate housing, which is also referred to as IMC (intermediate casing), also reduces or eliminates axial deflections, for example during a bird strike.
  • Another advantage of the embodiment according to the invention with the two-part construction of the inner ring lies in the possibility of joint processing of the two ring segments.
  • the recesses for the storage of the guide blade feet can be drilled together.
  • the two ring segments can be clamped or fixed to each other with a corresponding tool, after which the recesses can be bored correspondingly precisely.
  • the recesses can be positioned more accurately, which together with the screwing of the inner ring to the intermediate housing leads to additionally reduced relative movements by tolerances or thermal movements during operation between the two ring segments.
  • the blade positioning and thus their aerodynamic properties can be further improved.
  • the first ring segment upstream with respect to a primary flow of the turbomachine and the second ring segment is to be arranged downstream with respect to the primary flow.
  • the first and second ring segments are axially separated and arranged one after another in the flow direction. This facilitates the assembly and disassembly of the ring segments.
  • the first ring segment is arranged directly on the intermediate housing, while the second ring segment in turn abuts the first ring segment downstream.
  • first and the second ring segment having a plurality of pairs of mutually aligned mounting holes, through which a screw of the screw is guided to the intermediate housing.
  • both the first and the second ring segment can be screwed together with the intermediate housing, which leads to a particularly high mechanical stability.
  • the common screw also improves a correct relative alignment of the two ring segments to each other.
  • the first ring segment floating on the second ring segment and mounted on the intermediate housing and the second ring segment is bolted to the intermediate housing and / or that the first ring segment on the second ring segment, on the intermediate housing and in the Recesses to be arranged bearing elements of the guide vanes is to support.
  • the second ring segment is screwed to the intermediate housing, while the first ring segment is floatingly mounted or fixed only indirectly via the second ring segment on the intermediate housing or clamped on the intermediate housing.
  • the first ring segment comprises a groove in which a projection of the second ring segment is arranged. This simplifies during assembly, the relative positioning of the two ring segments to each other and increases in the assembled state, the mechanical stability of the inner ring in addition.
  • the projection is not positively received in the groove to allow thermally and / or mechanically related relative movements, volume changes, etc. of the two ring segments.
  • the first ring segment is sealed off via a radially outer and / or a radially inner sealing element, in particular an O-ring, against the intermediate housing and / or against the second annular segment.
  • a radially outer and / or a radially inner sealing element in particular an O-ring
  • the first and second ring segments are configured by a corresponding radial seat such that the first ring segment requires only one sealing element for the radially inner or the radially outer seal, as this saves additional manufacturing and assembly costs.
  • the inner ring is screwed from a downstream side and / or from an upstream side to the intermediate housing.
  • This allows a high degree of design flexibility.
  • at least the second ring segment of the inner ring is screwed only from the downstream side, as this allows an advantageous and cost-effective assembly and disassembly of the inner ring without complete disassembly of the entire inner ring system or the bearing housing.
  • At least one of the ring segments comprises at least one receptacle for the arrangement of a brush seal.
  • at least one and preferably at least the second ring segment is adapted to carry a brush seal, wherein the brush seal can be fixed or fixed in the receptacle, for example by means of a mechanical clamp.
  • a suitable brush seal comprises a brush seal housing, which consists of a support plate and a cover plate, which are interconnected and together surround at least one brush head of the brush seal system U-shaped and secure against falling out of the brush seal housing.
  • the cover plate or upstream in the flow direction region of the two-part brush seal housing is intended to discourage disturbing flow influences on a brush head from the brush head and protruding from the Bürstendichtungsgephase brush package, while downstream considered in the flow direction support plate of the brush seal housing serves as a support member, which is a bending of the brush pack in the axial direction of the aircraft engine is to prevent due to the pressure difference across the brush seal housing.
  • the first and / or second ring segment in the region of the receptacle comprises means for axially supporting the brush seal.
  • a stop for a structurally simple manner Element of the brush seal for example, be provided for the brush seal housing, which on the one hand facilitates the assembly of the brush seal and on the other hand, the load capacity of the brush seal are additionally increased.
  • the first and the second ring segment are aligned via at least one dowel pin relative to each other and / or relative to a circumferential direction of the intermediate housing.
  • a second aspect of the invention relates to an inner ring for an inner ring system according to the first aspect of the invention.
  • the inner ring is divided axially into a first and a second ring segment, which in the assembled state together form recesses for supporting radially inner end regions of guide vanes of the inlet guide vane ring, at least the second ring segment having mounting openings for screwing to the intermediate housing of the inner ring system.
  • This allows the inner ring improved aerodynamic properties and a reduction in maintenance costs of the inner ring system.
  • a third aspect of the invention relates to an intermediate housing for an inner ring system according to the first aspect of the invention.
  • the intermediate housing comprises mounting openings for screwing at least the second ring segment of the inner ring of the inner ring system. This allows the intermediate housing improved aerodynamic properties and a reduction in maintenance costs of the inner ring system.
  • a fourth aspect of the invention relates to a turbomachine, in particular an aircraft engine.
  • the turbomachine comprises an inner ring system according to the first aspect of the invention and an inlet guide vane having a plurality of vanes each having a radially outer and a radially inner end region with respect to a rim longitudinal axis, wherein the radially inner end portions of the vanes in common through the first and the second ring segment of the inner ring formed recesses are arranged.
  • the turbomachine has improved aerodynamic properties and can be serviced at a lower cost.
  • the guide vanes of the concludesleitschaufelkranzes are also referred to as IGV (inlet guide vanes), while their radially inner end portions can also be referred to as blade feet. Further features and their advantages can be found in the descriptions of the first, second and third aspect of the invention, with advantageous embodiments of the first, second and third aspect of the invention to be regarded as advantageous embodiments of the fourth aspect of the invention and vice versa.
  • the guide vanes are adjustable and / or that the radially inner end regions of the guide vanes are held in the recesses via bearing bushes.
  • the guide vanes in the region of their blade root eg inner journal or blade plate
  • the bushings may be clamped in the recesses, for example. With the help of bushings storage, tightness and mounting of the vanes can be advantageously improved. Due to the smaller by the screwing of the inner ring relative movements of the ring segments, the bushings are also subjected to significantly less wear.
  • the inner ring system and the inlet guide vane ring are part of a low-pressure compressor stage and / or a medium-pressure compressor stage and / or a high-pressure compressor stage and / or a high-pressure turbine stage and / or a medium-pressure turbine stage and / or a low-pressure turbine stage of the turbomachine.
  • the inner ring system is part of a first stage of a ND, MD and / or HP compressor or a ND, MD, and / or HP turbine turbomachine.
  • Fig. 1 shows a schematic section of a turbomachine 10 according to the invention in the region of a first stage of a compressor 12.
  • the turbomachine 10 is in the present case designed as an aircraft engine.
  • Compressor 12 which may be, for example, a single or multi-stage low, medium or high pressure compressor, includes as first stage an inlet guide vane 14 having a plurality of inlet guide vanes 16 (IGV) on a Kranzlteilsachse A each comprise a radially outer end portion (not shown) and a radially inner end portion 18, wherein the end portion 18 may also be referred to as a blade root.
  • the radially inner end regions 18 of the guide vanes 16 are arranged together with respective bearing bushes 20 in recesses 22.
  • the recesses 22 are formed together by a first ring segment 24a and a second ring segment 24b of an axially divided inner ring 26.
  • the first ring segment 24a is arranged upstream with respect to a primary flow of the turbomachine 10 and the second ring segment 24b is arranged downstream with respect to the primary flow.
  • the inner ring 26 is bolted to an intermediate housing 28 (IMC) for receiving structural loads.
  • the first ring segment 24a and the second ring segment 24b a plurality of spaced around the circumference of the intermediate housing 28 pairs aligned mounting holes 30a, 30b, through which a screw 32 to the intermediate housing 28 and in a corresponding, in this case with a thread provided mounting opening 30c of the intermediate housing 28 is screwed.
  • other fastening variants such as lock nuts or the like may be provided.
  • the screwing takes place here from the downstream side of the inner ring 26 ago. This advantageously allows the disassembly of the ring segments 24a, 24b without complete disassembly of the entire bearing structure.
  • the first ring segment 24a in the illustrated embodiment comprises a groove 34 in which a projection 36 of the second ring segment 24b is arranged with play. This restricts relative movability of the second ring segment 24b in relation to the first ring segment 24a, which increases the mechanical stability and facilitates the assembly of the inner ring 26.
  • the first ring segment 24a is connected to the intermediate housing 28 via a radially outer sealing element 38 designed as an O-ring sealed.
  • a radially lower seal may be eliminated since the seal for the air system is via the radial seating between the front and rear ring segments 24a, 24b. The elimination of a seal leads to lower costs, both in the manufacture and in the maintenance of the turbomachine 10th
  • the second ring segment 24b further comprises in the region of its downstream end a receptacle 40, in which a brush seal 42 is mounted, via which a seal of the inner ring 26 with respect to a rotor 44 of the compressor 12 is achieved.
  • the brush seal 42 comprises a brush seal housing 46, which is fixed in the receptacle 40 via two clamping plates 48.
  • the second ring segment 24b in the region of the receptacle 40 comprises a stop 50 for the axial support of the brush seal 42.
  • first and second ring segments 24a, 24b may be aligned via at least one locating pin (not shown) relative to each other or relative to a circumferential direction of the intermediate housing 28.
  • Fig. 2 shows a schematic section of an alternative embodiment of the turbomachine 10 according to the invention in the region of a first stage one compressor 12.
  • the basic structure corresponds to that in connection with Fig. 1 discussed.
  • the first ring segment 24a no groove 34 or recess.
  • the second ring segment 24b has no projection 36.
  • Fig. 3 shows a schematic section of another alternative embodiment of the turbomachine 10 according to the invention in the region of a first stage of a compressor 12.
  • the inner ring 26 in the present example only on the second Ring segment 24b is bolted to the intermediate housing 28.
  • the first ring segment 24a is in contrast floating and is secured in position via the screwed second ring segment 24b, the bearing bush 20, the blade root 18 and the intermediate housing 28.
  • the screwing of the second ring segment 24a with the intermediate housing 28 takes place in contrast to the previous embodiments of the upstream side of the inner ring 26, so that the second ring segment 24b has a corresponding internal thread in its mounting hole 30b.
  • the first ring segment 24a has a radially upper and a radially lower sealing element 38, which are each formed as an O-ring.
  • the basically optional stop 50 is shown in dashed lines.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15198116.4A 2015-12-04 2015-12-04 Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés Active EP3176386B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15198116.4A EP3176386B1 (fr) 2015-12-04 2015-12-04 Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
US15/363,914 US10494942B2 (en) 2015-12-04 2016-11-29 Inner ring system for an inlet guide vane cascade of a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15198116.4A EP3176386B1 (fr) 2015-12-04 2015-12-04 Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés

Publications (2)

Publication Number Publication Date
EP3176386A1 true EP3176386A1 (fr) 2017-06-07
EP3176386B1 EP3176386B1 (fr) 2021-01-27

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EP15198116.4A Active EP3176386B1 (fr) 2015-12-04 2015-12-04 Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés

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Country Link
US (1) US10494942B2 (fr)
EP (1) EP3176386B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10900367B2 (en) * 2016-02-24 2021-01-26 Borgwarner Inc. Sealing unit for turbocharger
US10704411B2 (en) 2018-08-03 2020-07-07 General Electric Company Variable vane actuation system for a turbo machine
US11725533B2 (en) * 2020-11-10 2023-08-15 Pratt & Whitney Canada Corp. Variable guide vane assembly and bushing ring therefor
CN115387906B (zh) * 2022-05-12 2024-04-16 中国航发四川燃气涡轮研究院 低进口轮毂比发动机的进气承力框架连接结构及装配方法

Citations (6)

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Publication number Priority date Publication date Assignee Title
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
EP1319844B1 (fr) 2001-12-13 2009-12-02 Rolls-Royce Deutschland Ltd & Co KG Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz
EP2261467A2 (fr) * 2009-06-05 2010-12-15 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
EP2472066A1 (fr) * 2010-12-30 2012-07-04 Rolls-Royce Corporation Aubage statorique à géométrie variable pour moteur à turbine à gaz et moteur à turbine à gaz associé
WO2014046965A1 (fr) * 2012-09-20 2014-03-27 United Technologies Corporation Module de système d'engrenage d'entraînement de soufflante et mécanisme d'accouplement d'aube de guidage d'entrée
DE102014205986A1 (de) * 2014-03-31 2015-10-01 MTU Aero Engines AG Leitschaufelkranz, Leitschaufel, Innenring und Strömungsmaschine

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Publication number Priority date Publication date Assignee Title
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
US2917329A (en) * 1955-05-13 1959-12-15 City Nat Bank And Trust Compan Rotary seal
US5114159A (en) * 1991-08-05 1992-05-19 United Technologies Corporation Brush seal and damper
US9140133B2 (en) * 2012-08-14 2015-09-22 United Technologies Corporation Threaded full ring inner air-seal
EP2725200B1 (fr) 2012-10-25 2018-06-06 MTU Aero Engines AG Stator et turbomachine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
EP1319844B1 (fr) 2001-12-13 2009-12-02 Rolls-Royce Deutschland Ltd & Co KG Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz
EP2261467A2 (fr) * 2009-06-05 2010-12-15 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
EP2472066A1 (fr) * 2010-12-30 2012-07-04 Rolls-Royce Corporation Aubage statorique à géométrie variable pour moteur à turbine à gaz et moteur à turbine à gaz associé
WO2014046965A1 (fr) * 2012-09-20 2014-03-27 United Technologies Corporation Module de système d'engrenage d'entraînement de soufflante et mécanisme d'accouplement d'aube de guidage d'entrée
DE102014205986A1 (de) * 2014-03-31 2015-10-01 MTU Aero Engines AG Leitschaufelkranz, Leitschaufel, Innenring und Strömungsmaschine
WO2015149732A2 (fr) * 2014-03-31 2015-10-08 MTU Aero Engines AG Couronne d'aubes fixes, bague intérieure et turbomachine

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Publication number Publication date
US20170159470A1 (en) 2017-06-08
US10494942B2 (en) 2019-12-03
EP3176386B1 (fr) 2021-01-27

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