EP3203035A1 - Système d'aube directrice d'une turbomachine - Google Patents

Système d'aube directrice d'une turbomachine Download PDF

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Publication number
EP3203035A1
EP3203035A1 EP17153139.5A EP17153139A EP3203035A1 EP 3203035 A1 EP3203035 A1 EP 3203035A1 EP 17153139 A EP17153139 A EP 17153139A EP 3203035 A1 EP3203035 A1 EP 3203035A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
guide vane
turbomachine
recess
securing element
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
EP17153139.5A
Other languages
German (de)
English (en)
Other versions
EP3203035B1 (fr
Inventor
Joachim Wulf
Frank Stiehler
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
Publication of EP3203035A1 publication Critical patent/EP3203035A1/fr
Application granted granted Critical
Publication of EP3203035B1 publication Critical patent/EP3203035B1/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
    • 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
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a stator blade system for a turbomachine according to the preamble of patent claim 1. Furthermore, the invention relates to a turbomachine and a method for assembling a stator blade system for a turbomachine.
  • a stator for a turbomachine in which in the circumferential direction of the stator adjacent to each other, to its radially extending longitudinal axis adjustable vanes are provided. Radial inside of the vanes, an inner ring is arranged. The vanes are mounted at their radially inner end in respective recesses of the inner ring. At least one of the guide vanes has a sliding surface formed substantially perpendicular to the longitudinal axis and arranged radially inward. The sliding surface and the inner ring form a friction pairing. As a result, respective leaks in the bearing of the guide vane on the inner ring are particularly reduced.
  • the object of the present invention is to improve a fuse of a stator blade system for a turbomachine. It is another object of the invention to improve a turbomachine and to provide a particularly simple method for mounting a guide vane system for a turbomachine.
  • a first aspect of the invention relates to a stator blade system for a turbomachine having at least one guide blade rotatably mounted about an adjustment axis, which is arranged with a radially inner end portion in a corresponding recess of an inner ring, wherein the arrangement of the guide blade is secured to the inner ring by means of a securing element form fit ,
  • the securing element is designed as an elongated element, which extends at least in a circumferential direction of the turbomachine recess and / or passage opening of the radially inner end portion of the vane and at least in a circumferential direction of the turbomachine recess and / or passage opening of the Inner ring is arranged.
  • This backup represents a reliable positive connection of a Leitschaufelzapfens with the inner ring. A leaking of the inner ring, for example, in the case of so-called pump surges is thus particularly unlikely or even completely excluded.
  • no additional leakage paths in the axial direction are opened by the respective recesses and / or passage openings, since these extend in the circumferential direction.
  • the positive connection of the inner ring with the vane also suppresses the known as Cording thermal deformation of the inner ring. This prevents unnecessary wear of respective sealing elements arranged on the inner ring.
  • the cording is caused in particular by transient thermal deformations of the inner ring and / or the guide vanes.
  • the vane system can be part of a vane ring, which is also referred to as a stator.
  • the guide blade system can comprise a plurality of guide vanes which are rotatably mounted about an adjustment axis and which are arranged next to one another in the circumferential direction.
  • the respective adjustment axis of the guide vanes preferably corresponds to a radial direction of the turbomachine.
  • the guide vane or the guide vanes are mounted on the inner ring and / or the inner ring is held on the guide vanes.
  • the securing element is designed such that it prevents a relative, radial movement of the guide vanes and the inner ring to each other or at least limited to a certain maximum dimension by the arrangement in the respective recesses and / or through holes.
  • the respective recesses and / or passage openings can be designed so that either the guide blade with the securing element can be rotated together within the inner ring about the adjustment axis or the guide vane can be rotated without the securing element must be rotated.
  • the vane can thus continue to be set or rotated in a predetermined angular range, whereby the turbomachine can be operated at any operating point with a particularly high efficiency.
  • the vane system is installed in a low pressure compressor or high pressure compressor of aircraft engines.
  • the vane of the vane system may be formed at its radially inner end portion frusto-conical. This construction is characterized by a very low radial height. This allows a leakage-optimal design of respective inner cavities of the inner ring and the flow machine and thus overall structurally favorable design of a rotor assembly. In contrast, with a radially inner end region, which is designed as a bearing journal and is encompassed by the inner ring, increases in leakage are to be expected. In particular, it may be necessary in this case to form the inner ring split axially. In addition, the recesses and / or passage openings can be aligned with each other.
  • respective passage openings and / or recesses are arranged at least in partial overlap to each other so as to be able to guide the securing element in the circumferential direction through this recess and / or passage opening.
  • the passage openings and / or recesses are preferably shaped so that the guide vane is still adjustable.
  • a fuse element can be used to jointly secure a plurality or all of the vanes.
  • the effort to secure the arrangement of the vanes on the inner ring decreases considerably. It is no longer necessary to separately secure each vane separately.
  • a fuse element can be inserted in the circumferential direction in the inner ring. This securing element can extend over the entire extent in the circumferential direction of the inner ring.
  • the common securing of a plurality of guide vanes by means of a common securing element is made possible only by the orientation of the respective recess and / or passage opening in the circumferential direction of the turbomachine in this simple form.
  • the recess of the guide vane is designed as a groove running on the outside at least partially around the radially inner end region of the vane.
  • a groove is fast and inexpensive to manufacture.
  • the groove running on the circumference of the radially inner end region of the guide blade has an advantageous effect on the vibration behavior of the guide blade during operation of the turbomachine.
  • the risk of leakages generated by the fuse is minimized in a groove extending only in regions around the radially inner end region of the guide vane.
  • the securing element may be supported radially outwardly and / or inwardly.
  • the securing element is designed as extending in the circumferential direction, round in cross-section or rectangular fuse wire.
  • a fuse wire is a particularly inexpensive to produce and / or very lightweight fuse element.
  • a safety wire can be particularly easily adapted to the shape or the radius of the inner ring.
  • the respective recesses and / or passage openings may at least partially have a corresponding cross-section.
  • An angular, in particular a rectangular cross-section and an angular, in particular rectangular security wire are particularly inexpensive to manufacture.
  • a round cross section and / or a round safety wire are particularly robust. In particular, there are no stress peaks due to sharp angles in the radially inner end region of the guide blade and / or in the inner ring.
  • the inner ring is undivided in the axial direction of the turbomachine.
  • Such an inner ring is particularly inexpensive to manufacture, requires no additional connecting elements in the axial direction during assembly and has no leakage through a gap extending in the circumferential direction.
  • Such an axially undivided inner ring is particularly advantageous when the radially inner end portion of the vane is frusto-conical.
  • an end region shaped in this way can be introduced without any problems into the corresponding recess of the inner ring.
  • no additional sleeves for supporting the guide vane on the inner ring are then necessary.
  • the inner ring is divided in the circumferential direction of the turbomachine into at least two inner ring segments.
  • the guide vane system may include an inner ring having two inner ring segments extending over 180 °.
  • the inner ring is composed of four 90-degree inner ring segments.
  • a divided in the circumferential direction inner ring allows a particularly simple installation of the turbomachine.
  • such a particularly large inner ring may be provided, whose diameter is not limited by respective manufacturing equipment to a maximum diameter of a manufacturable component.
  • a circumferentially divided inner ring allows a particularly simple insertion of the fuse element. The fuse element can easily into an opening on a front side of the respective inner ring segments - that is, a surface which faces the next inner ring segment in the assembled inner ring - are threaded.
  • a respective securing element is provided per inner ring segment.
  • the respective securing elements can be mounted particularly easily when the inner rings are divided in the circumferential direction.
  • a part of the guide blade system, consisting of an inner ring segment, the respective associated guide vanes and the associated securing element, are mounted and then then simply the inner ring and thus the Leitschaufelsystem assembled by connecting these inner ring segments with the guide vanes and the already mounted securing elements become.
  • the inner ring is at least partially manufactured by means of an additive manufacturing process.
  • an additive manufacturing process is particularly suitable for being able to produce an undivided inner ring in the axial direction with complex recesses and / or passage openings.
  • the respective guide vanes and / or the securing element are at least partially manufactured by means of an additive manufacturing process. In particular, it is thus possible to manufacture the inner ring and the securing element and / or the guide vanes in a common production, in particular in a single production step.
  • At least one sealing element is arranged radially inwardly on the inner ring.
  • a flow space of the turbomachine can be sealed against a shaft of the turbomachine arranged radially on the inside. Due to the positive securing of the guide vanes on the inner ring, as already explained, there is no or only a particularly reduced cording. As a result, wear of this sealing element during operation of the turbomachine is particularly reduced.
  • a seal carrier for holding the sealing element. This ensures easy replacement of the sealing element.
  • the recess and / or the passage opening of the radially inner end portion of the vane is formed at least partially elongated corresponding to the securing element and / or the recess and / or the passage opening of the inner ring at least partially corresponding longitudinally is formed to the securing element.
  • the securing element can be supported particularly reliably on the respective recesses and / or passage openings.
  • a second aspect of the invention relates to a turbomachine, in particular an aircraft engine.
  • this turbomachine comprises at least one guide vane system according to the first aspect of the invention.
  • a third aspect of the invention relates to a method for mounting a guide vane system for a turbomachine.
  • the provision of at least one guide vane which can be rotatably mounted about an adjustment axis and has a radial end region which has at least one recess and / or passage opening extending in the installation position of the vane in the circumferential direction of the turbomachine, of an inner ring with a recess corresponding to the radially inner end region of the vane and provided with at least one in the circumferential direction of the turbomachine recess and / or passage opening, and formed as an elongate element securing element.
  • the guide vane is rotatably mounted on the turbomachine, in particular on an outer ring of the turbomachine or a guide vane ring.
  • the introduction of the radially inner end portion of the guide vane in the Recess of the inner ring provided.
  • the securing element is inserted into the recess and / or into the passage opening of the inner ring and into the recess and / or into the passage opening of the guide blade for the positive securing of the arrangement of the guide blade on the inner ring.
  • the securing element is inserted.
  • the securing element can be inserted in the circumferential direction in the respective recesses and / or through holes.
  • a fuse element designed as a fuse element is adapted only by this insertion of the circumferentially curved shape of the inner ring.
  • a sufficiently long securing element can be performed by a plurality of recesses and / or through holes of a plurality of vanes, whereby they can be secured together with a single securing element.
  • the method according to the third aspect of the invention is suitable for mounting a guide vane system according to the first aspect of the invention, wherein the guide vane system can be mounted so easily.
  • the method for mounting according to the third aspect of the invention can thus also be used as part of a method for assembling a turbomachine according to the second aspect of the invention.
  • the features and advantages resulting from the guide vane system according to the first aspect of the invention or from the turbomachine according to the second aspect of the invention can be taken from the descriptions of the first and the second aspect of the invention, wherein the advantageous embodiments of the first and the second aspect of the invention as advantageous embodiments of the third aspect of the invention to look at the other way around.
  • Fig. 1 1 shows in a meridian section a stator blade system 10 for a turbomachine with at least one guide blade 14 rotatably mounted about an adjustment axis 12, which is arranged with a radially inner end region 16 in a corresponding recess 18 of an inner ring 20.
  • the radially inner end region 16 is of frustoconical design.
  • the arrangement of the guide vane 14 on the inner ring 20 is thereby secured by a form-fitting means of a securing element 22. Because of this securing of the arrangement, it is prevented that the radially inner end region 16 of the guide blade 14, for example due to so-called pumping surges, jumps off the inner ring 20 or slips out of its recess 18.
  • the guide vane system 10 has an outer ring 24 on which the vane 14 is rotatably supported by a bearing pin 26.
  • each adjusting means for rotating the vane 14 may be provided about the adjustment axis 12.
  • the turbomachine is designed as an aircraft engine.
  • a coordinate system 30 is shown for orientation.
  • the arrow 32 marks the radially outward direction of the turbomachine.
  • the arrow 34 marks the axial direction of the turbomachine. Since it is a meridian section, the circumferential direction of the turbomachine points in and out of the plane of the sheet and follows a curvature of the inner ring 20 Fig. 2 to Fig. 6 is the coordinate system 30 also shown.
  • Fig. 2 is the circumferential direction of the turbomachine indicated by arrow 46.
  • the vane system 10 forms part of a so-called vane ring relationship of a so-called stator of the turbomachine.
  • the vane ring comprises a plurality of circumferentially juxtaposed vanes 14.
  • the vane system 10 and the vane ring is preferably a part of a high pressure or low pressure compressor of the turbomachine.
  • a sealing element 36 Radially inside a sealing element 36 is provided on the inner ring 20.
  • a flow space which is limited by the outer ring 24 and the inner ring 20, are sealed against other parts of the turbomachine.
  • the sealing element 36 may be formed, for example, as a grinding brush seal, by means of which this flow space is sealed to a rotating shaft of the turbomachine.
  • the securing element 22 is formed as an elongated element, which is arranged at least in a running in the circumferential direction of the turbomachine through hole 38 of the radially inner end portion 16 of the guide vane 14.
  • the orientation of the securing element 22 in the circumferential direction and also in each case corresponding recesses and / or through holes 40 is a single or common fuse one or more vanes 14 on the inner ring 20 by means of a single securing element 22 possible.
  • this fuse is particularly easy to assemble and requires very few parts.
  • the inner ring 20 is held particularly reliably on the guide blade 14 due to the secure arrangement and respective transient thermal effects, which are also referred to as cording, are reduced. As a result, wear of the sealing element 36 during operation of the turbomachine is particularly low.
  • the guide vanes 14 and the inner ring 20 are supported radially to each other outwardly and / or inwardly.
  • the passage opening 40 or the passage openings 40 of the inner ring 20 are in the schematic perspective view of the guide vane system 10 according to Fig. 2 shown. It can also be seen there that the passage opening 38 of the guide blade 14 and the passage opening 40 of the inner ring 20 are aligned with each other for the assembly or insertion of the securing element 22. Since the respective passage openings 38, 40 extend in the circumferential direction, due to the securing of the arrangement of the guide blade system 10, there are preferably no additional axial leakages.
  • FIG. 2 Shown embodiment of the guide vane system 10 shows passage openings 40 of the inner ring 20, which have a rectangular cross-section.
  • a securing element 22, not shown here preferably likewise has a rectangular cross-section, in order to be able to support itself particularly well in the passage opening 40.
  • the passage opening 38 of the vane 14 may have a rectangular cross-section.
  • the cross sections 38, 40 of the passage openings 38, 40 and the securing element 22 are designed such that they have a total of at least a minimum clearance to ensure the adjustability of the guide vane 14.
  • the passage openings 38, 40 and / or the securing element 22 may also have a round cross-section. A round cross-section leads to particularly low stress peaks under load, whereby the guide vane system 10 is particularly robust.
  • Other cross-sectional shapes for the passage openings 38, 40 and the securing element 22 can be selected.
  • Fig. 3 to 6 show in a schematic sectional view of the radially inner end portion 16 of the vane 14 with the fuse element 22 arranged therein in various embodiments.
  • Fig. 3 shows the embodiment according to Fig. 1 ,
  • the securing element 22 as well as the passage opening 38 in the radially inner end region 16 of the guide vane 14 is rectangular.
  • the cross section of the passage opening 38 is opposite the cross section of the fuse element 22 in the axial direction increases. This ensures the adjustability of the guide vane 14.
  • Fig. 4 shows an embodiment in which the securing element 22 is arranged in a recess 42 on the guide blade 14.
  • the recess 42 according to Fig. 4 it is as outside at least partially around the radially inner end portion 16 of the guide vane 14 extending groove.
  • a corresponding groove for receiving a further region of the securing element 22 is formed on the inside of the recess 18 (not shown). This configuration in turn ensures that the guide vane 14 can continue to be rotated about the adjustment axis 12 without this rotation being blocked by the securing element 22.
  • the securing element 22 also has a round cross section.
  • Fig. 5 shows a recess 42 which is formed as completely around the radially inner end portion 16 extending groove.
  • a corresponding groove for receiving a further region of the securing element 22 is formed on the inside of the recess 18 (not shown).
  • the completely circumferential groove does not restrict an adjustment range during the rotation of the guide blade 14.
  • the securing element 22 also has a round cross section.
  • Fig. 6 shows a further embodiment in which the recess 42 similar to the recess 42 according to Fig. 4 is trained.
  • the recess 42 is rectangular.
  • the securing element 22 is rectangular in cross-section.
  • FIG. 2 an inner ring segment 44 of the inner ring 20 is shown. At least two of these inner ring segments 44 form the inner ring 20.
  • the inner ring 20 is divided in the circumferential direction.
  • the securing element 22 is simply guided in the divided inner ring 20 in the circumferential direction through the respective passage openings 40 of the inner ring segment 44.
  • the guide vanes 14 have previously been arranged with their radially inner end region 16 in the recess 18 of the inner ring segment 44. It can be provided per inner ring segment 44 each have a securing element 22. The use of a single, circumferential securing element 22 is possible.
  • this fuse wire can be provided as a straight wire and be adapted only by the threading to a curvature of the inner ring 20.
  • the inner ring 20 or the inner ring segments 44 can also have respective recesses 42, for example in the form of a groove.
  • This groove could, for example, point radially inward, as a result of which a further radially outward support of the securing element 22 in such a groove of the inner ring 20 is then possible.
  • a shape and / or a cross section of a passage opening 40 or a recess 42 of the inner ring 20 to the shapes and / or cross sections of the fuse element 22 and / or the recess 42 of the guide vane 14 and / or the passage opening 38 of the guide vane 14 correspond.
  • exemplary shapes and cross sections is on the Fig. 3 to Fig. 6 directed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17153139.5A 2016-02-05 2017-01-25 Système d'aube directrice d'une turbomachine Active EP3203035B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016201766.7A DE102016201766A1 (de) 2016-02-05 2016-02-05 Leitschaufelsystem für eine Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP3203035A1 true EP3203035A1 (fr) 2017-08-09
EP3203035B1 EP3203035B1 (fr) 2020-01-15

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EP17153139.5A Active EP3203035B1 (fr) 2016-02-05 2017-01-25 Système d'aube directrice d'une turbomachine

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US (1) US10450888B2 (fr)
EP (1) EP3203035B1 (fr)
DE (1) DE102016201766A1 (fr)

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CN114658694B (zh) * 2020-12-23 2024-05-14 上海电气电站设备有限公司 一种燃气轮机可调导叶的装配方法

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EP1586744A2 (fr) * 2004-04-14 2005-10-19 General Electric Company Aubes de guidage variables pour turbine à gaz
EP2716874A1 (fr) * 2012-10-08 2014-04-09 MTU Aero Engines GmbH Stator, procédé de montage et turbomachine
EP2884055A1 (fr) 2013-12-10 2015-06-17 MTU Aero Engines GmbH Aubes de guidage variable avec cône tronqué dans un ensemble palier
EP2960438A1 (fr) * 2014-06-26 2015-12-30 MTU Aero Engines GmbH Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170226887A1 (en) * 2016-02-05 2017-08-10 MTU Aero Engines AG Guide vane system for a turbomachine
US10450888B2 (en) * 2016-02-05 2019-10-22 MTU Aero Engines AG Guide vane system for a turbomachine

Also Published As

Publication number Publication date
DE102016201766A1 (de) 2017-08-10
US10450888B2 (en) 2019-10-22
EP3203035B1 (fr) 2020-01-15
US20170226887A1 (en) 2017-08-10

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