EP3176388B1 - Segment d'aube directrice à sécurité radiale - Google Patents

Segment d'aube directrice à sécurité radiale Download PDF

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Publication number
EP3176388B1
EP3176388B1 EP16201368.4A EP16201368A EP3176388B1 EP 3176388 B1 EP3176388 B1 EP 3176388B1 EP 16201368 A EP16201368 A EP 16201368A EP 3176388 B1 EP3176388 B1 EP 3176388B1
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EP
European Patent Office
Prior art keywords
radial
guide vane
securing element
vane segment
shroud
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
EP16201368.4A
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German (de)
English (en)
Other versions
EP3176388A1 (fr
Inventor
Markus Schlemmer
Manfred Feldmann
Rudolf Stanka
Oliver Thiele
Bernd Kislinger
Manuel Hein
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3176388A1 publication Critical patent/EP3176388A1/fr
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Publication of EP3176388B1 publication Critical patent/EP3176388B1/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
    • B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/10—Manufacture by removing material

Definitions

  • the present invention relates to a stator segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud, which extend along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud a plurality of stator blades are arranged side by side in the circumferential direction, which are materially connected to the inner shroud and the outer shroud, in particular integrally connected, wherein the outer shroud in an axial longitudinal direction comprises an axially forward end wall element and an axially rear end wall element, such that the outer shroud and the two end walls in longitudinal section form a trough-like profile, wherein at least one radial securing element is provided on the axially rear end wall, which is adapted to the guide vane segment in the radial direction re To secure to a surrounding housing, wherein the radial securing element is formed as a projection having
  • US2015 / 0125289 A1 shows a vane segment with a trough-like outer shroud, on the rear end wall of radial securing elements are arranged.
  • the radial securing elements have bearing portions with bearing surfaces which lie on a cylindrical peripheral surface. To make this curved surface must be milled from the full, resulting in significant overhead and higher cost of the component.
  • Similar vane segments are off EP 2 811 118 A1 and EP 1 431 517 A2 known.
  • vane segments which may also be referred to as vane clusters
  • vane clusters for improved and simplified assembly of vane segments, which may also be referred to as vane clusters, in a gas turbine engine, it has been found that the provision of radial securing elements is an apt alternative to heretofore known hook fuses.
  • stator vane segment In the radial securing of vane segments, which are usually combined in a gas turbine to form a vane ring, it is particularly important to secure the vane segments within the turbine housing in the radial direction against falling out.
  • the stator vane segment In operation of the gas turbine, the stator vane segment is generally acted upon by the flow to which the vane (s) is exposed, typically a moment which is such that the axially rearward end wall member is forced radially outward, whereas the axially forward one End wall element is pulled radially inward. This moment is taken up by the axially rear end wall element, that the radially outer edge of the same is supported on the housing.
  • the turbomachine if the turbomachine is out of operation, the flow acting on the vanes in the gas duct is missing.
  • the radial fail safe or the radial securing element described here is used. In this way, it is prevented that the guide blade segment can fall out, for example due to gravity, when the turbo
  • the object of the invention is to provide a vane segment, the radial securing element enables a simplified manufacturing.
  • the support section has a bearing surface which lies in a first plane whose normal vector has vector components in the circumferential direction and in the axial direction (AR) and / or in the radial direction (RR).
  • the first plane is in space so as to intersect a tangential plane to the circumferential direction in a plane defined by the radial direction and the circumferential direction. If the normal vector has a vector component in the circumferential direction and in the radial direction (or in the axial and radial directions), the first plane has no curvature in the circumferential direction and can be made simpler by this simplified geometry or shaping.
  • the vane segment in the circumferential direction (UR) on the outer shroud has two shroud side surfaces arranged at a distance from one another, which are designed such that they can come into contact with a shroud side surface of an adjacent guide blade segment, wherein the radial securing element is flush with at least one shroud side surface is trained.
  • the guide vane segment in the circumferential direction to each other at a distance arranged comprise two radial securing elements, so that the guide vane segment is supported defined at two points and can not slip out of the intended position, in particular can not rotate about a radially extending axis.
  • the one radial securing element is formed flush with the one side of the shroud, and that the other radial securing element is arranged at a distance to the other shroud side surface.
  • the distance measured in the circumferential direction of the two radial securing element is smaller than the distance measured in the circumferential direction of the two shroud side surfaces.
  • the radial securing element is produced by linear grinding.
  • Linear grinding enables the movement of a corresponding grinding tool along a main direction of the grinding, and along a feed direction orthogonal thereto. Due to the tool geometry and the linear movement process (grinding main direction), a bearing surface whose normal vector has the abovementioned features can be formed in a simple manner by the linear grinding.
  • the support section has a second surface which lies in a second plane whose normal vector has vector components in the circumferential direction and in the radial direction (RR), in particular also in the axial direction (AR).
  • the second surface and the support surface are inclined to each other, wherein the angle formed by the first and the second plane in a sectional plane which is spanned by the radial direction (RR) and the axial direction (AR), in an area between 70 ° and 90 °, preferably 75 ° to 85 °.
  • the vane segment may further comprise a circumferential securing element in the circumferential direction in a central region of the rear end wall.
  • the step of aligning the blank vane segment and the step of abrading may be performed once for each raw radial-securing member when two or more raw radial securing members are provided on the blank vane segment.
  • the step of aligning the blank vane segment relative to the linear sander is performed such that the linear sander can be moved or spaced apart from other components of the blank vane segment as the raw radial securing element is abraded, in particular at a distance to a circumferentially provided in a central region on the rear end wall circumferential securing element or a corresponding raw circumferential securing element.
  • the linear grinding of the radial securing elements can be adapted for different guide blade segments of different turbine stages or different gas turbines, so that the bearing surface of the radial securing element can be produced by appropriate relative orientation of the guide blade segment and the linear grinding tool and can the linear grinding device not be in contact with other components or components, in particular projections and reinforcing ribs of the vane segment comes into contact.
  • the invention also relates to a gas turbine, in particular an aircraft gas turbine comprising at least one turbine stage with a plurality of vane segments arranged side by side in the circumferential direction, so that they form a turbine blade vane ring, wherein the vane segments have at least one of the features described above.
  • the vane segment according to the invention is defined in claim 1.
  • the inventive method for producing a vane segment is defined in claim 12.
  • the gas turbine according to the invention is defined in claim 15.
  • Fig. 1 shows in a simplified perspective view of a vane segment 10 with a radially inner shroud 12 and a radially outer shroud 14 in the radial direction RR extending between the inner shroud 12 and the outer shroud 14 vanes 16, wherein the number of three vanes 16 shown here for a vane segment 10 is purely exemplary; it is also possible for two, four, five or more vanes to be provided in a vane segment 10.
  • the vane segment 10 of Fig. 1 is shown so that the view of the suction sides 18 and the trailing edges 20 of the guide vanes 16 is released.
  • the radially outer shroud 14 comprises an axially front end wall 22 and an axially rear end wall 24.
  • the two end walls 22, 24 are designed inclined to the shroud 14 so that there is a trough-like profile in a longitudinal section.
  • a radial securing element 26 can be seen, which is formed on the rear end wall 24 and protrudes therefrom against the axial direction AR or against the main flow direction in the turbomachine.
  • Fig. 2 shows a simplified longitudinal sectional view through the outer shroud 14 and a portion of a turbine housing connected to the nozzle segment 10 turbine housing 28.
  • the radial securing element 26 can be seen, which is designed as a projection and projecting against the axial direction AR of the rear end wall 24.
  • the radial securing element 26 has an essentially S-shaped support section 27 with a convex and a concave arc, against which straight pieces or surfaces adjoin.
  • counterpart 30 is formed so that between the radial securing element 26 and the counterpart 30 a system is made possible for radial securing of the vane segment 26 on the housing 30th
  • Fig. 3 shows the in Fig. 2 dashed rimmed area III, so that from this the radial securing element 26 with its support portion 27 and the counterpart 30 of the turbine housing 28 are better visible.
  • the radial securing element 26 comprises at its support portion 27 a support surface 32 and a second surface 34.
  • the counterpart 30 has a contact surface 36 which faces the support surface 32 of the radial securing element 26 lies.
  • the support surface 32 and the second surface 34 are formed inclined to each other, and in the plane of the drawing (plane, which is spanned by the axial direction AR and the radial direction RR) include an angle ⁇ , preferably about 70 ° 90 °, in particular about 75 ° to 85 °.
  • the contact surface 36 on the counterpart 30 of the housing 28 has substantially the same inclination, as the support surface 32. The interaction between the contact surface 32 and the abutment surface 36 allows the securing of the vane segment 10 in the radial direction RR.
  • FIG. 4 Figure 3 is a simplified perspective view of a blank vane segment 10a after casting such a workpiece.
  • outer shroud 14 front end wall 22, rear end wall 24, and the guide vanes 16.
  • two raw radial securing elements 26a and 26b can be seen, which act as a kind of thickened projection against the axial direction AR protrude from the rear end wall 24.
  • a circumferential securing element 40 formed from two ribs can be seen, which is also still in its raw form after casting.
  • the linear grinding process is carried out until the radial securing element 26 or its support section 27 has reached its final shape, in particular the support surface 32 and the second surface 34 are formed.
  • Starting from the raw vane segment 10a of Fig. 4 show the Fig. 5 a view in which the linear grinding device 42, the raw radial securing elements 26 b processed, and in Fig. 6 a representation in which the linear grinding device 42, the raw radial securing element 26 a processed. From each other Raw radial securing element 26a or 26b, which may already be present as a finished radial securing element 26, is in Fig. 5 respectively. Fig. 6 only one upper section visible.
  • the guide vane segment 10 in the region of the outer shroud 14 respective shroud side surfaces 46 which are adapted to that adjacent vane segments 10 may abut each other in the mounted state in the gas turbine.
  • the vane segment 10 in each case has two shroud side surfaces 46, wherein each shroud side surface 46 may be assigned a radial securing element 26.
  • the respective radial securing element 26 may be flush with the shroud side surface 46, as exemplified by the Fig. 5 or even the Fig. 1 is apparent.
  • the radial securing element 26 may be disposed to the shroud side surface 46 at a distance AB, as best shown in FIG Fig. 4 is apparent, but also in the Fig. 6 is indicated in the in the Fig. 6 left radial securing element 26 (26 a), which is shown in contact with the linear grinding device 42.
  • the linear grinding device in the contact region with the radial securing element 26 is not guided tangentially to the curvature formed in this contact region (along the circumferential direction UR) of the shroud 14 or the rear end wall 24. Rather, an angle ⁇ is formed between a longitudinal axis LAS representing the grinding direction of the linear grinding device 42 and the tangential direction TR in the region of the radial securing element 26.
  • the support surface 32 or / and the surface 34 formed by means of the linear grinding device 42 have normal vectors which, in addition to at least one vector component in the axial direction AR and / or radial direction RR, also have a vector component in the circumferential direction UR.
  • Such relative positioning of linear grinder 42 and vane segment 10 relative to one another enables material to be removed from the radial securing elements 26 without the linear grinding device coming into contact with other components of the vane segment 10, particularly with the circumferential securing element 40 also along the circumferential direction UR is provided on the rear end wall 24 and protrudes counter to the axial direction AR thereof.
  • Fig. 7 shows a simplified schematic sectional view approximately along the section line VII-VII of Fig. 6 .
  • the linear grinding device 42 is designed in the region of its grinding surfaces 44 in such a way that it has a contour complementary to the radial securing element 26 or its bearing section 27.
  • this complementary grinding contour it is possible that, by means of linear relative movement of the linear grinding device 42 along the longitudinal axis LAS of the linear grinding device, a successive material removal on a raw radial securing element 26a, 26b (FIG. Fig. 4 ) takes place until the finished radial securing element 26 is formed.
  • a rather complex milling of the radial securing element (s) 26 can be dispensed with compared to the linear grinding.
  • Fig. 8 shows in the sub-figures A) and B) two highly simplified schematic sectional views of the support surface 32 of the radial securing element 26 to illustrate the vector components of the normal vector.
  • Fig. 8A is a longitudinal section, as he also from the Fig. 1 it can be seen, wherein only the support surface 32 is shown as a line with the normal vector NV, and the vector components VRR and VAR in the radial or axial direction.
  • Fig. 8B is a section corresponding to the line VIII-VIII of Fig. 3 , wherein the bearing surface 32 is shown hatched as a line and a portion of the cut radial securing element 26.
  • the normal vector NV with the vector components VRR and VUR in the radial direction or circumferential direction which are shown in this illustration, is shown for the bearing surface 32.
  • the radial securing elements should therefore be able to be produced inexpensively, which makes possible by means of linear grinding is, and provide a safeguard against falling out in the radial direction, in particular in the assembly / disassembly of stator segments of a turbine stage of a gas turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Segment d'aube directrice (10) destiné à une turbine à gaz, plus précisément à une turbine à gaz d'avion, comprenant
    au moins un anneau de renforcement radialement extérieur (14) et un anneau de renforcement radialement intérieur (12), qui s'étendent sur un arc de cercle respectif et forment ensemble une section annulaire,
    plusieurs aubes directrices (16) étant juxtaposées dans la direction circonférentielle (UR) entre l'anneau de renforcement extérieur (14) et l'anneau de renforcement intérieur (12) dans la direction radiale (RR), lesquelles aubes directrices sont reliées par une liaison de matière, en particulier d'une seule pièce, à l'anneau de renforcement intérieur (12) et à l'anneau de renforcement extérieur (14),
    l'anneau de renforcement extérieur (14) comprenant dans une direction longitudinale axiale (AR) un élément de paroi frontale axialement avant (22) et un élément de paroi frontale axialement arrière (24) de sorte que l'anneau de renforcement extérieur (14) et les deux parois frontales (22, 24) forment un profil en forme de cuvette en coupe longitudinale,
    au moins un élément de fixation radiale (26) étant prévu sur la paroi frontale axialement arrière (24), lequel est conçu pour immobiliser le segment d'aube directrice (10) dans la direction radiale (RR) par rapport à un boîtier périphérique (28, 30).
    l'élément de fixation radiale (26) ayant la forme d'une saillie comportant une partie d'appui (27), qui est conçue pour être soutenue par une pièce homologue correspondante (30) au niveau du boîtier (28),
    caractérisé en ce que
    la partie d'appui (27) possède une surface d'appui (32) se trouvant dans un plan dont le vecteur normal comporte une composante de vecteur (VUR) dans la direction circonférentielle (UR) et dans la direction radiale (RR).
  2. Segment d'aube directrice selon la revendication 1, caractérisé en ce que la partie d'appui (27) possède une surface d'appui (32) se trouvant dans un plan dont le vecteur normal comporte une composante de vecteur (VAR) dans la direction axiale (AR).
  3. Segment d'aube directrice selon la revendication 1 ou 2, caractérisé en ce qu'il possède dans la direction circonférentielle (UR), au niveau de l'anneau de renforcement extérieur (14), deux surfaces latérales d'anneau de renforcement (46), disposées à une certaine distance l'une de l'autre, qui sont conçues de manière à pouvoir venir en contact avec une surface latérale d'anneau de renforcement d'un segment d'aube directrice adjacent, l'élément de fixation radiale (26) étant réalisé à niveau avec au moins une surface latérale d'anneau de renforcement (46).
  4. Segment d'aube directrice selon la revendication 3, caractérisé en ce qu'il comprend deux éléments de fixation radiale (26) positionnés à une certaine distance l'un de l'autre dans une direction circonférentielle.
  5. Segment d'aube directrice selon la revendication 4, caractérisé en ce qu'un élément de fixation radiale (26) est réalisé à niveau avec une surface latérale d'anneau de renforcement (46) et en ce que l'autre élément de fixation radiale (26) est positionné à une certaine distance (AB) par rapport à l'autre surface latérale d'anneau de renforcement (46).
  6. Segment d'aube directrice selon la revendication 4 ou 5, caractérisé en ce que la distance, mesurée dans la direction circonférentielle, des deux éléments de fixation radiale (26) est inférieure à la distance, mesurée dans la direction circonférentielle, des deux surfaces latérales d'anneau de renforcement (46).
  7. Segment d'aube directrice selon une des revendications précédentes, caractérisé en ce que l'élément de fixation radiale (26) est réalisé par des boucles linéaires.
  8. Segment d'aube directrice selon une des revendications précédentes, caractérisé en ce que la partie d'appui (27) possède une deuxième surface d'appui (34) se trouvant dans un deuxième plan dont le vecteur normal comporte des composantes de vecteur dans la direction circonférentielle et dans la direction axiale (RR).
  9. Segment d'aube directrice selon la revendication 8, caractérisé en ce que le vecteur normal du deuxième plan comporte des composantes de vecteur dans la direction axiale (AR).
  10. Segment d'aube directrice selon la revendication 8 ou 9, caractérisé en ce que la deuxième surface (34) et la surface d'appui (32) sont inclinées l'une par rapport à l'autre, l'angle (β) qui est formé par le premier et le deuxième plan et qui se trouve dans un plan de coupe défini par la direction radiale (RR) et la direction axiale (AR), étant situé dans une plage de 70 ° à 90 °, de préférence de 75° à 85°.
  11. Segment d'aube directrice selon l'une des revendications précédentes, caractérisé en ce qu'il comporte un élément de fixation circonférentielle (40) dans une zone centrale de la paroi frontale arrière (24) dans la direction circonférentielle (UR).
  12. Procédé de réalisation d'un segment d'aube directrice (10) destiné à une turbine à gaz, plus précisément à une turbine à gaz d'avion, le procédé comprenant les étapes suivantes :
    Fournir un segment d'aube directrice brut (10a) comprenant au moins un anneau de renforcement radialement extérieur (14) et un anneau de renforcement radiale intérieur (12), qui s'étendent chacun sur un arc de cercle et forment ensemble une section annulaire, plusieurs aubes directrices (16) étant juxtaposées dans la direction circonférentielle (UR) entre l'anneau de renforcement extérieur (14) et l'anneau de renforcement intérieur (12) dans la direction radiale (RR), lesquelle aubes directrices sont reliées par une liaison de matière, en particulier d'une seule pièce, à l'anneau de renforcement intérieur (12) et à l'anneau de renforcement extérieur (14),, l'anneau de renforcement extérieur (14) comprenant dans une direction longitudinale axiale (AR) un élément de paroi frontale axialement avant (22) et un élément de paroi frontale axialement arrière (24) de sorte que l'anneau de renforcement extérieur (14) et les deux parois frontales (22, 24) forment un profil en forme de cuvette en coupe longitudinale, et avec au moins un élément de fixation radiale brut (26a, 26b) ;
    Orienter le segment d'aube directrice brut par rapport à un dispositif de meulage linéaire (42) de façon à ce que de la matière de l'élément de fixation radiale brut (26a, 26b) puisse être enlevée par le dispositif de meulage linéaire (42) ;
    Meuler l'élément de fixation radiale brut (26a, 26b) au moyen du dispositif de meulage linéaire (42) jusqu'à ce que l'élément de fixation radiale brut (26a, 26b) prenne la forme d'un élément de fixation radiale (26) muni d'une partie d'appui (27) qui possède une surface d'appui (27) qui se situe dans un premier plan, dont le vecteur normal comporte des composantes de vecteur dans la direction circonférentielle et dans la direction radiale (RR), notamment aussi dans la direction axiale (AR).
  13. Procédé selon la revendication 12, dans lequel l'étape d'orientation du segment d'aube directrice brut (26a, 26b) et l'étape de meulage sont effectuée chacune une fois pour l'élément de fixation radiale brut respectif (26a, 26b), lorsque deux ou plusieurs éléments de fixation radiale bruts (26a, 26b) sont prévus sur le segment d'aube directrice brut (10a).
  14. Procédé selon la revendication 12 ou 13, dans lequel l'étape d'orientation du segment d'aube directrice brut (10a) par rapport au dispositif de meulage linéaire (42) est réalisée de façon à ce que le dispositif de meulage linéaire (42) puisse être guidé ou déplacé à une certaine distance des autres composants du segment d'aube directrice brut (10a) lors du meulage de l'élément de fixation radiale brut (26a, 26b), notamment à une certaine distance, dans la direction circonférentielle (UR), d'un élément de fixation circonférentielle (40) prévu dans une zone centrale sur la paroi frontale arrière (24) ou d'un élément de fixation circonférentielle brut correspondant.
  15. Turbine à gaz, en particulier turbine à gaz d'avion, comprenant au moins un étage de turbine muni de plusieurs éléments d'aube directrice (10) selon l'une des revendications 1 à 11, qui sont positionnés les uns à côté des autres dans une direction circonférentielle de façon à former une couronne d'aubes directrices de l'étage de turbine.
EP16201368.4A 2015-12-04 2016-11-30 Segment d'aube directrice à sécurité radiale Active EP3176388B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015224378.8A DE102015224378A1 (de) 2015-12-04 2015-12-04 Leitschaufelsegment mit Radialsicherung

Publications (2)

Publication Number Publication Date
EP3176388A1 EP3176388A1 (fr) 2017-06-07
EP3176388B1 true EP3176388B1 (fr) 2018-11-14

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US (1) US10370989B2 (fr)
EP (1) EP3176388B1 (fr)
DE (1) DE102015224378A1 (fr)
ES (1) ES2700953T3 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016202519A1 (de) * 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine

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Publication number Priority date Publication date Assignee Title
US6893217B2 (en) * 2002-12-20 2005-05-17 General Electric Company Methods and apparatus for assembling gas turbine nozzles
DE602004003757T2 (de) * 2003-07-23 2007-10-11 Alstom Technology Ltd. Verfahren zur Aufbereitung und Verfahren zur Herstellung einer Turbinenschaufel
PL2615243T3 (pl) 2012-01-11 2017-12-29 MTU Aero Engines AG Segment wieńca łopatkowego do maszyny przepływowej i sposób jego wytwarzania
FR2990719B1 (fr) * 2012-05-16 2016-07-22 Snecma Distributeur de turbomachine, et procede de fabrication
JP5962915B2 (ja) * 2012-10-29 2016-08-03 株式会社Ihi タービンノズルの固定部構造及びこれを用いたタービン
ES2664322T3 (es) * 2013-06-06 2018-04-19 MTU Aero Engines AG Segmento de álabes directores de una turbomáquina y una turbina
US9835038B2 (en) * 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
DE102013224199A1 (de) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
GB201417150D0 (en) * 2014-09-29 2014-11-12 Rolls Royce Plc Carriers for turbine components

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Publication number Publication date
US20170159466A1 (en) 2017-06-08
US10370989B2 (en) 2019-08-06
ES2700953T3 (es) 2019-02-20
DE102015224378A1 (de) 2017-06-08
EP3176388A1 (fr) 2017-06-07

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