EP3208426B1 - Segment d'aube directrice pour turbomachine - Google Patents

Segment d'aube directrice pour turbomachine Download PDF

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Publication number
EP3208426B1
EP3208426B1 EP16203029.0A EP16203029A EP3208426B1 EP 3208426 B1 EP3208426 B1 EP 3208426B1 EP 16203029 A EP16203029 A EP 16203029A EP 3208426 B1 EP3208426 B1 EP 3208426B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
flange
seal carrier
support surface
turbomachine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16203029.0A
Other languages
German (de)
English (en)
Other versions
EP3208426A1 (fr
Inventor
Markus Schlemmer
Manfred Feldmann
Rudolf Stanka
Oliver Thiele
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 EP3208426A1 publication Critical patent/EP3208426A1/fr
Application granted granted Critical
Publication of EP3208426B1 publication Critical patent/EP3208426B1/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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • 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
    • 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
    • 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
    • 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
    • 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
    • F05D2240/55—Seals

Definitions

  • the invention relates to a guide vane element for a turbomachine, in particular for an aircraft engine. Further aspects of the invention relate to a guide vane segment having such a guide vane element, a guide vane ring having at least one guide vane segment, and a turbomachine.
  • a gas turbine stage which has a sealing ring element mounted on a guide blade root by means of a spoke centering device.
  • This spoke centering device has an inner wall and a circumferential groove receiving the spoke centering device.
  • the inner wall has an end face facing an inner surface of the circumferential groove and an adjacent flank angled towards it.
  • a rounded portion is formed as a radius between the end face and the flank. If, during normal use of the gas turbine stage, the front end face in the flow direction comes into contact with the inner surface of the groove, this radius reduces the stress load and wear.
  • a low-pressure turbine which has a plurality of stator stages.
  • Honeycomb structures are arranged at the respective radial ends of the stator stages to form a sealing point with low fluid leakage with labyrinth seals radially opposite them on a shaft housing.
  • the US 4,194,869 a vane cluster with fastening means for securing the position of the vane cluster in a gas turbine. This position securing can reduce any flow around the vane cluster at undesired locations.
  • EP 2 559 849 A2 A guide vane segment for a turbomachine is known.
  • the guide vane segment comprises at least one guide vane element with a flange and a positioning means protruding therefrom.
  • a partial surface of the positioning means is beveled relative to a support surface of the flange.
  • a radially outer region of the positioning means rests against a seal carrier of the guide vane segment.
  • the object of the present invention is to improve a guide vane element, a guide vane segment, a guide vane ring and a turbomachine of the type mentioned above, so that these components have a high tightness against fluid leakage even under heavy loads.
  • the present invention comprises a guide vane element according to claim 1 for a guide vane segment and a guide vane segment with the guide vane element according to the invention and with a seal carrier according to claim 2.
  • a partial surface of the positioning means borders the flange, and respective surface normals of the support surface and the partial surface enclose an angle with each other that is different from a zero angle, wherein the partial surface is designed such that it does not come into contact with the seal carrier.
  • the transition from the flange to the positioning means can be formed, for example, as a straight line or as a curved line, at which the flange and the partial surface can adjoin one another.
  • the transition can also be formed as an edge, for example with a rounded edge, at which the flange and the partial surface adjoin one another.
  • the inclusion of an angle other than a zero angle by the respective surface normals of the support surface and the partial surface means that the partial surface is offset from the support surface, at least in some regions. Accordingly, when the guide vane segment is used as intended as a component of a turbomachine, the partial surface is set back and/or beveled relative to the support surface in a main flow direction of a working medium flowing through the turbomachine during operation.
  • the partial surface and the support surface can also form at least part of a shoulder on the flange.
  • the support surface can thus be designed as a sealing surface running radially around the flange, relative to which the partial surface is set back and/or beveled.
  • SIAS Static Inner Air Seal
  • a beveled and/or recessed partial surface of the positioning device ensures that even in the event of a load-related relative movement between the SIAS and the guide vane element, the SIAS does not lift off the support surface, especially since the SIAS cannot be disadvantageously supported on the positioning device.
  • tilting of the SIAS around the positioning device is prevented and, in contrast to prior art solutions, a high degree of tightness against fluid leakage is achieved even under heavy loads.
  • the guide vane segment which comprises a guide vane element according to the invention and a seal carrier, can correspond to a part of a guide vane ring and can be designed, for example, as a guide vane ring segment. Accordingly, the guide vane segment can be designed, for example, as a third and thus as a 120° segment of such a guide vane ring.
  • the guide vane segment can comprise, for example, a radially inner shroud segment, a guide vane blade or multiple guide vane blades, as well as a radially outer shroud segment.
  • the seal carrier can have a sealing element, for example in the form of a brush seal or a honeycomb seal, at one radial end.
  • the support surface is designed as an annular surface segment.
  • the support surface can be defined by a circular arc or, in some areas, by a straight line instead of a circular arc. This allows a particularly uniform surface pressure to be achieved between the seal carrier and the support surface. This has the The advantage is that a uniform sealing effect on the support surface can be achieved even under dynamic loads on the seal carrier.
  • the positioning means is connected to the flange as a single piece. This reduces the number of individual parts required to construct the guide vane element. This is advantageous because the guide vane segment can thus be manufactured with particularly low assembly effort.
  • the forked arrangement of the positioning pins can also be referred to as spoke centering.
  • the forked design prevents any rotation of the seal carrier around the two positioning pins. This allows a simple way to restrict a further degree of freedom of movement of the seal carrier.
  • a guide vane element according to the invention achieves a particularly high sealing effect between the support surface and a seal carrier supported on it.
  • the present invention further encompasses a guide vane ring comprising at least one guide vane segment according to the invention.
  • the guide vane ring can, for example, be composed of three 120° guide vane segments. Such a guide vane ring contributes in an improved manner to reducing fluid leakage.
  • the present invention also encompasses a turbomachine, in particular an aircraft engine, with at least one guide vane segment according to the invention and additionally or alternatively with at least one guide vane element according to the invention and additionally or alternatively with at least one guide vane ring.
  • a turbomachine can be operated with reduced fluid leakage and thus with a particularly high degree of efficiency.
  • the turbomachine is a turbine, and the support surface of the flange faces a main flow direction of a working medium flowing through the turbomachine during operation.
  • the turbomachine is a compressor
  • the support surface of the flange faces away from the main flow direction of a working medium flowing through the turbomachine during operation. This can at least largely prevent any possible lifting of the seal carrier from the support surface, even in a compressor.
  • Fig. 1 shows a guide vane segment 50 for a turbomachine, known from the prior art.
  • the guide vane segment 50 has a flat sealing surface 54 at a sealing area 52, against which a radial seal (not shown here) can be brought into contact.
  • the guide vane segment 50 has a serrated centering 56 for the radial seal.
  • the sealing surface 54 extends in this case over a particularly large, Fig. 1 hatched area, which also includes a partial surface area of individual centering elements of the serrated centering 56.
  • the sealing surface 54 extends up to a linear contact 57 of the centering 56.
  • the contact 57 extends over two centering struts 58 of the centering 56, which are arranged in a fork-like manner.
  • the contact 57 can also be referred to as a support point on an edge area of the sealing surface 54. Due to the extension of the sealing surface 54 to the centering struts 58 and thus to areas of the centering 56, increased fluid leakage can occur between the sealing surface 54 and the radial seal if the sealing surface 54 and the radial seal are at an unfavorable angle to one another due to operational loads. This is due to the fact that the radial seal tilts around the contact 57 on the centering as a result of operational deformations.
  • a guide vane element 12 is shown, which in Fig. 2b in a side view according to a Fig. 2a shown in the direction of view A indicated by an arrow together with a seal carrier 30.
  • the guide vane element 12 and the seal carrier 30 belong to a Fig. 2b A partially illustrated guide vane segment 10 for a turbomachine (not shown in detail here), which may be configured, for example, as an aircraft engine.
  • the guide vane segment 10 thus comprises the guide vane element 12 and the seal carrier 30.
  • a guide vane ring (not shown in detail here) can be assembled from several such guide vane segments 10 and used in the turbomachine.
  • the guide vane element 12 comprises in the present case at least one blade 36, a radially inner shroud segment 34, and a radially outer shroud segment not shown here.
  • the guide vane element 12 comprises a flange 14 formed in a radial direction of extension R of the guide vane element 12 and at least one positioning means 18 protruding from the flange 14 in the radial direction of extension R.
  • the positioning means 18 is integrally connected to the flange 14.
  • the guide vane segment is Fig. 2b pushed along an assembly direction M onto the presently annular seal carrier 30, so that the seal carrier 30 and the flange 14 abut one another.
  • the flange 14 has a support surface 16, on which the seal carrier 30 is supported in its contact with the flange 14.
  • the support surface 16 of the flange 14 faces a main flow direction H of a working medium flowing through the turbomachine during operation, provided the turbomachine is designed as a turbine. In the case of a turbomachine designed as a compressor, however, the support surface 16 of the flange 14 would face away from the main flow direction H.
  • the support surface 16 serves as a sealing surface with which the seal carrier 30 forms a sealing seat when arranged and supported on the flange 14.
  • the support surface 16 is designed here as an annular surface segment.
  • the support surface can be delimited by a circular arc or, in some regions, by a straight line instead of a circular arc. This particularly includes the fact that the support surface 16 can also be delimited in the radial direction of extension R by a transition 19, designed, for example, as a straight line, and accordingly has no circumferential radial rounding at such a delimiting point and deviates slightly from a ring segment shape.
  • a partial surface 20 of the positioning means 18 borders the flange 14, wherein respective surface normals 17, 21 of the support surface 16 and the partial surface 20 enclose an angle ⁇ with each other that is different from a zero angle.
  • the first surface normal 17 is assigned to the support surface 16, whereas the second surface normal 21 is assigned to the partial surface 20.
  • the seal carrier 30 has a circumferential radial groove 32, with which the positioning means 18 engages when the seal carrier 30 is arranged on the flange 14.
  • the seal carrier 30 can be secured to the flange 14 by means of the fixing element shown, which in this case is designed as a bolt 28, as soon as the seal carrier 30 is brought into contact with the support surface 16.
  • the positioning means 18 in this case has two positioning pins 22, 24 arranged in a fork-like manner relative to one another, which engage in the circumferential radial groove 32 when the seal carrier 30 is arranged on the flange 14.
  • the bolt 28 can be passed through a recess 26 partially delimited by the two positioning pins 22, 24.
  • the positioning pins 22, 24 can each also be referred to as a "tang.”
  • the partial surface 20 of the positioning mandrel 22 and thus of the positioning means 18 directly borders the transition 19.
  • the surface normals 17, 21 enclose the angle ⁇ , which can also be referred to as the so-called "tang angle.”
  • Fig. 2b While the subarea in Fig. 2b shown embodiment is designed as a straight surface which is bevelled relative to the support surface 16, the embodiment according to Fig. 3 a curved course of the partial surface 20 and thus a curvature of the partial surface 20.
  • Fig. 4a The illustrated embodiment ensures that the seal carrier 30 can lie flat on the support surface 16 without coming into contact with the partial surface 20 and thus the positioning means 18. This ensures that the seal carrier 30 is arranged on the support surface 16 under a high surface pressure and thus with a particularly good sealing effect.
  • Fig. 4a It is shown that the guide vane element 12 may have a shoulder which is Fig. 4b is shown enlarged according to a detailed view B. The paragraph extends over a flange surface 15 of the flange 14 adjacent to the support surface 16.
  • the support surface 16 creates an uninterrupted contact surface segment that runs along the guide vane element 12 in some areas and on which a sealing seat can be formed with the seal carrier 30 (SIAS).
  • SIAS seal carrier 30
  • a radial position of a vertex of the angle ⁇ can be - as in Fig. 2b shown - lie on the transition 19, with the partial surface 20 adjoining the support surface 16 at a bevelled angle.
  • the angle ⁇ can also, as in Fig. 3 shown, change over the course of the partial surface 20. Because the surface normals 17, 21 of the support surface 16 or the partial surface 20 enclose the angle ⁇ which is different from the zero angle, an offset results between the support surface 16 and the partial surface 20 in the main flow direction H. This offset makes it possible to allow operational deformations of the SIAS (seal carrier 30) without these deformations causing the seal carrier 30 to lift off the support surface 16.
  • Additional local projections which may be adjacent to the support surface 16 surrounding the guide vane element 12, can also be provided with the angle ⁇ , so that the SIAS has space for operational deformations and the local projections are not touched by the SIAS during deformation.
  • the term "projections” includes elements that protrude radially inward (in the radial direction of extension R) with respect to the support surface 16 (sealing surface on the flange 14).
  • the term "projections” includes, for example, anti-rotation devices or sprues.
  • the present invention can prevent the SIAS from being deformed in the main flow direction H around a linear system 57 known from the prior art (on the Fig. 1 shown centering 56) tilts, thereby forming a flat, conical gap between the SIAS and the support surface 16. When this gap occurs, increased fluid leakage can occur in systems known from the prior art.

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

Claims (7)

  1. Élément d'aube de guidage (12) pour un segment d'aube de guidage (10) comportant l'élément d'aube de guidage (12) et un support d'étanchéité (30), dans lequel l'élément d'aube de guidage (12) comprend une bride (14) formée dans une direction d'extension radiale (R) de l'élément d'aube de guidage (12), laquelle bride présente une surface de soutien (16) permettant de disposer et de soutenir un support d'étanchéité (30), et comprend au moins un moyen de positionnement (18) faisant saillie depuis la bride (14) dans la direction d'extension radiale (R) et permettant d'orienter le support d'étanchéité (30) par rapport à l'élément d'aube directrice (12), dans lequel le moyen de positionnement (18) présente au moins deux mandrins de positionnement (22, 24) disposés en forme de fourche l'un par rapport à l'autre et conçus pour venir en prise dans une rainure radiale périphérique (32) du support d'étanchéité (30) lorsque le support d'étanchéité (30) est disposé sur la bride (14),
    et dans lequel, dans une transition entre la bride (14) et le moyen de positionnement (18), une surface partielle (20) du moyen de positionnement (18) est adjacente à la bride (14) et des normales de surface (17, 21) respectives de la surface de soutien (16) et de la surface partielle (20) forment entre elles un angle (α) différent d'un angle zéro, dans lequel la surface partielle (20) est décalée et/ou biseautée par rapport à la surface de soutien et n'entre pas en contact avec le support d'étanchéité (30) dans le cas du segment d'aube directrice (10), caractérisé en ce que la surface de soutien (16) est conçue comme un segment de surface annulaire.
  2. Segment d'aube de guidage (10) pour une turbomachine, en particulier pour un moteur d'aéronef, comportant :
    - au moins un élément d'aube de guidage (12) selon la revendication 1,
    - au moins un support d'étanchéité (30) qui est disposé sur la bride (14) et qui est orienté par rapport à l'élément d'aube directrice (12) à l'aide du moyen de positionnement (18), dans lequel la bride (14) présente une surface de soutien (16) sur laquelle est soutenu le support d'étanchéité (30), dans lequel les au moins deux mandrins de positionnement (22, 24) disposés en forme de fourche l'un par rapport à l'autre viennent en prise dans une rainure radiale périphérique (32) du support d'étanchéité (30) lorsque le support d'étanchéité (30) est disposé sur la bride (14), et
    dans lequel la surface partielle (20) n'est pas en contact avec le support d'étanchéité (30).
  3. Segment d'aube directrice (10) selon la revendication 2,
    caractérisé en ce que le moyen de positionnement (18) est relié d'un seul tenant à la bride (14).
  4. Couronne d'aubes directrices, comprenant au moins un segment d'aube directrice (10) selon l'une des revendications 2 à 3.
  5. Turbomachine, en particulier moteur d'aéronef, comportant au moins un segment d'aube directrice (10) selon la revendication 2 ou 3 et/ou comportant au moins un élément d'aube directrice (12) selon la revendication 1 et/ou comportant au moins une couronne d'aubes directrices selon la revendication 4.
  6. Turbomachine selon la revendication 5, caractérisée en ce que la turbomachine est une turbine et la surface de soutien (16) de la bride (14) est tournée vers une direction d'écoulement principale (H) d'un fluide de travail s'écoulant à travers la turbomachine lors du fonctionnement de celle-ci.
  7. Turbomachine selon la revendication 5, caractérisée en ce que la turbomachine est un compresseur, et la surface de soutien (16) de la bride (14) est opposée à une direction d'écoulement principale (H) d'un fluide de travail s'écoulant à travers la turbomachine lors du fonctionnement de celle-ci.
EP16203029.0A 2016-02-18 2016-12-08 Segment d'aube directrice pour turbomachine Active EP3208426B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016202519.8A DE102016202519A1 (de) 2016-02-18 2016-02-18 Leitschaufelsegment für eine Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP3208426A1 EP3208426A1 (fr) 2017-08-23
EP3208426B1 true EP3208426B1 (fr) 2025-04-30

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Application Number Title Priority Date Filing Date
EP16203029.0A Active EP3208426B1 (fr) 2016-02-18 2016-12-08 Segment d'aube directrice pour turbomachine

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Country Link
US (1) US10895162B2 (fr)
EP (1) EP3208426B1 (fr)
DE (1) DE102016202519A1 (fr)
ES (1) ES3032768T3 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017221660A1 (de) * 2017-12-01 2019-06-06 MTU Aero Engines AG Modul für eine Strömungsmaschine
DE102020200073A1 (de) * 2020-01-07 2021-07-08 Siemens Aktiengesellschaft Leitschaufelkranz
DE102020203840A1 (de) 2020-03-25 2021-09-30 MTU Aero Engines AG Gasturbinenbauteil
DE102020115106B4 (de) 2020-06-08 2022-08-25 Man Energy Solutions Se Turbinenleitapparat

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DE102016202519A1 (de) 2017-08-24
US20170241279A1 (en) 2017-08-24
ES3032768T3 (en) 2025-07-24
EP3208426A1 (fr) 2017-08-23
US10895162B2 (en) 2021-01-19

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