EP3075960B1 - Unité d'aubes directrices à profils aérodynamiques multiples - Google Patents

Unité d'aubes directrices à profils aérodynamiques multiples Download PDF

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Publication number
EP3075960B1
EP3075960B1 EP15161814.7A EP15161814A EP3075960B1 EP 3075960 B1 EP3075960 B1 EP 3075960B1 EP 15161814 A EP15161814 A EP 15161814A EP 3075960 B1 EP3075960 B1 EP 3075960B1
Authority
EP
European Patent Office
Prior art keywords
airfoil
guide vane
platform
platform member
vane unit
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.)
Not-in-force
Application number
EP15161814.7A
Other languages
German (de)
English (en)
Other versions
EP3075960A1 (fr
Inventor
Herbert Brandl
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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 Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Priority to EP15161814.7A priority Critical patent/EP3075960B1/fr
Priority to US15/084,145 priority patent/US20160290146A1/en
Priority to KR1020160038340A priority patent/KR20160117330A/ko
Priority to JP2016070822A priority patent/JP2016194300A/ja
Priority to CN201610194226.9A priority patent/CN106014495A/zh
Publication of EP3075960A1 publication Critical patent/EP3075960A1/fr
Application granted granted Critical
Publication of EP3075960B1 publication Critical patent/EP3075960B1/fr
Not-in-force 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting

Definitions

  • the present disclosure relates to a multi-airfoil guide vane unit as described in claim 1. It further relates to an airfoil member and a platform member for a guide vane unit of the described type.
  • vane twins, triplets or any multiples are required as they provide several benefits, such as, for instance, increased stiffness and lower platform leakage.
  • the multiples are cast in one piece. However, this requires complex tooling to enable precision cast and turns manufacturing expensive. Moreover, the cast yield rate of such multiples can be quite low for the big sizes required in stationary power generation turbines. Moreover, service deterioration of one single airfoil may require replacement and scrapping of an entire multi airfoil unit.
  • EP 1 176 284 A2 proposes a built multi-airfoil guide vane unit and to separately manufacture airfoil and platform members, and to join them by brazing. Separation after service for reconditioning purposes is difficult and expensive. Just like in one-piece casts, the whole arrangement is rigid and over-constrained, such that differential thermal expansion results in high thermal mismatch stresses, in turn limiting the service lifetime of the multi-vane unit.
  • US 5,797,725 discloses to receive an airfoil member in a platform or shroud in a floating manner such as to allow movement in response to thermal conditions.
  • US 5 421 703 A discloses a multi-airfoil guide vane unit, comprising a first platform member, a second platform member, and at least two airfoil members.
  • the airfoil members have a longitudinal extent along an airfoil span width and two longitudinal ends. All airfoil members are rigidly affixed to a platform member at a first longitudinal end and at least one airfoil member is rigidly affixed to both platform members at both longitudinal ends.
  • Other examples of known guide vanes are disclosed in US 4 834 613 A , in US 2010/111682 A2 , in WO 2014/158284 A2 and in US 2011/002787 A1 .
  • a multi-airfoil guide vane unit comprising a first platform member, a second platform member, and at least two airfoil members.
  • the airfoil members have a longitudinal extent along an airfoil span width and two longitudinal ends. All airfoil members are rigidly affixed to a platform member at a first longitudinal end and at least one airfoil member is rigidly affixed to both platform members at both longitudinal ends.
  • At least one of the airfoil members is floatingly connected to one of the platform members at a second longitudinal end, and a longitudinally floating joint arrangement is provided between the second longitudinal end of the airfoil member and the platform member, such as to allow displacement of the airfoil member relative to said platform member along the longitudinal extent of said airfoil member.
  • airfoil longitudinal direction may in particular be identical with a radial direction for the intended mounted state of the guide vane unit in a turbo-engine in case of an axial flow stage.
  • the multi-airfoil unit is less rigid and allows for relative movement between the members of the unit to account for differential thermal expansion.
  • the floating joint arrangement comprises a male joint feature provided at one of the second longitudinal end of the airfoil member and the platform member, and a female joint feature provided at the other one of the second longitudinal end of the airfoil member and the platform member, the male feature being received within said female feature.
  • the floating joint arrangement may particularly easy be provided.
  • the floating joint arrangement is intended for a defined displacement range, and the male member and female member are dimensioned such that the male member is at least with a part of its longitudinal extent received within the female member in a nominal built state as well as in all intended displaced positions.
  • the male joint feature is provided as a peg section at the second longitudinal end of the airfoil member and the female feature is a pocket provided in the platform member.
  • the male joint feature and in more specific embodiments a peg or the peg section may be particularly easy provided on the airfoil member, as the airfoil member is generally bar-shaped anyway.
  • the male feature outer surface is a ruled surface spanned by straight parallel lines. This will maintain a gap formed between the peg section and the lateral walls of the pocket constant along in all intended displacement positions.
  • a peg section provided at a longitudinal end of an airfoil member exhibits an airfoil-shaped cross section. This enables to avoid cross sectional jumps and other geometric discontinuities along the airfoil member longitudinal extent.
  • the male feature and the female feature are arranged and configured to form a running fit. That is, a narrow gap is provided between an outer boundary of the male feature and an inner boundary of the female feature. It will be appreciated, that the presence of the gap enables a free movement between the male feature and the female feature and thus the unconstrained displacement between the airfoil member and the platform member in one direction at the floating joint arrangement. Further, the narrower the gap is, the more constrained the airfoil member will be in all other directions. This constraint of movement in all other directions but the airfoil longitudinal direction may be found desirable in order to avoid oscillation modes incorporating an airfoil member end. Oscillation frequencies of the airfoil member are thus at least essentially maintained identical to those of a fully constrained airfoil member.
  • the running fit may be provided by a fitting member arranged within the female joint feature, wherein the fitting member is in particular provided as one of a bi-cast and an injection molding member. Said arrangement may serve to facilitate manufacturing.
  • the inner dimension of the female feature as such may be provided such as to provide a large clearance with the received male feature. This, in turn, means the female feature may be manufactured with a low demand as to accuracy. No high precision machining or manufacturing is required. Thus, providing the female feature as such is largely facilitated and is thus inexpensive.
  • a fitting member is produced within the female joint feature and embracing the male joint feature.
  • a concave form locking feature for instance a flute, is provided on inner walls of the female joint feature such that, when the fitting member is produced, the added material fills the gap between the female and the male joint features on the one hand, and at the same time creates a form lock with the walls of the female joint feature.
  • the fitting member is secured within the female joint feature.
  • Other appropriate concave and/or convex form-lock features in order to secure the fitting member may be provided inside the female joint feature.
  • the multi-airfoil guide vane unit is characterized in that a depth of the female joint feature is larger than a received length of the male joint feature such that a gap is provided between the bottom of the female joint feature and a tip of the male joint feature. Said feature enables improved longitudinal displacement capability, such that the male joint feature may displace deeper into the female feature if needed.
  • the multi-airfoil guide vane unit comprises three airfoils.
  • two outer airfoils are rigidly affixed to a platform member at both longitudinal ends and a middle airfoil member is rigidly affixed to a first platform member at one airfoil member end and is floatingly connected to the second platform member at the other airfoil member end.
  • the middle airfoil member is rigidly affixed to a platform member at both longitudinal ends, and each of two outer airfoil members is rigidly affixed to a platform member at its first end and is floatingly connected to a platform member at its second end.
  • both outer airfoil members may be rigidly affixed to the first platform member and floatingly connected to the second platform member, or a first outer airfoil member is rigidly affixed to the first platform member and is floatingly connected to the second platform member, and a second outer airfoil member is rigidly affixed to the second platform member and is floatingly connected to the first platform member.
  • an airfoil member wherein the male joint feature is provided in that a longitudinal end section of the airfoil member is provided with constant cross sections thus forming a generally cylindrical peg section.
  • a platform member wherein a female joint feature is provided in that the platform member comprises at least one pocket adapted and configured for receiving an airfoil member end section.
  • at least one concave form lock feature is provided on the side wall of the pocket, and is in particular provided as a circumferential groove, thus providing a form-lock feature for a fitting member, which fitting member serves to reduce play between the female joint feature and the male joint feature in the directions in which displacement is not desired.
  • FIG. 1 depicts a guide vane triplet 1.
  • the guide vane triplet comprises a radially inner platform member 14, a radially outer platform member 15, and three airfoil members 11, 12, and 13.
  • the airfoil members extend with their span width or longitudinal extent between the platform members.
  • Two outer airfoil members 11 and 13 are rigidly affixed to both platform members 14 and 15. Visible are braze or weld seams 16 at which airfoil members 11 and 13 are rigidly connected to the radially inner platform 14.
  • Airfoil members 11 and 13 are also rigidly connected to the radially outer platform 15, however, this is not visible in the present depiction. Airfoil members 11 and 13 are thus rigidly connected to a platform member on both respective longitudinal ends.
  • the middle airfoil member 12 is also at one longitudinal end rigidly connected to the radially outer platform member 15.
  • Airfoil member 12 is at its second end 121 floatingly connected to the radially inner platform member 14, in that the second end 121 is for instance received in a pocket 141 provided in the inner platform member 14. This allows displacement of the airfoil member 12 relative to the inner platform member 14 along the longitudinal extend of airfoil member 12.
  • a pocket 141 is provided as a female joint feature in the platform member 14.
  • the airfoil member 12 is at its longitudinal end 121 provided as a peg section 123, constituting a male joint feature.
  • the peg section is provided as a general cylinder, that is to say, the outer surface of the peg section is a ruled surface spanned by straight parallel lines.
  • Peg section 123 of airfoil member 12 is received in the pocket 141, with a gap provided between an inner surface of the pocket 141 and an outer surface of the peg section 123.
  • the airfoil member 12 may displace relative to the platform member 14 along the longitudinal direction indicated at 2 without changing the width of the gap between the peg section and the pocket.
  • Peg section 123 may exhibit an airfoil-shaped cross section, and thus constitute a continuation of the cross-sectional geometry of airfoil member 12, thus enabling to provide airfoil member 12 without cross sectional jumps or geometric discontinuities.
  • FIG. 3 a more detailed view of peg section 123 provided on an airfoil member end 121 and received in a pocket 141 of platform member 14 is shown.
  • An inner wall of the pocket is provided with a flute or other concave form locking feature 18, said flute in particular running around the circumference of the pocket.
  • a fitting member 17 is provided between the inner wall of the pocket 141 and an outer surface of the peg section 123, wherein said fitting member is arranged and configured to minimize lateral play of the peg section within the pocket.
  • Fitting member 17 is in a form-locked manner secured by concave form locking feature or flute 18 provided at the inner wall of pocket 141.
  • Said fitting member 17 and the peg-shaped end section 123 of the airfoil member 12 form a running fit with each other.
  • a minimum gap is still provided between the fitting member 17 and the peg -shaped end section of the airfoil 12, such as to allow a displacement of the airfoil member 12 relative to the platform member 14 along the longitudinal direction 2.
  • the fitting member 17 may in particular be manufactured for instance by bi-cast, as described for instance in US 5,797,725 , or metal injection molding, as described for instance in US 8,257,038 .
  • the peg-shaped end section 123 of the airfoil member 12 is inserted into the pocket 141, and subsequently material is introduced into the gap between the peg section outer surface and the pocket inner wall. Both processes mentioned above are known to create no metallurgical bonding between the bodies. Thus, the gap may be filled and the fitting member 17 may be produced which allows displacement of the airfoil member 12 inside the pocket 141 along the airfoil member longitudinal direction 2.
  • FIG 4 an alternative arrangement is shown, wherein the male joint feature 142 is arranged on the platform member 14 and received within the female joint feature 122 provided at an end 121 of the airfoil member 12.
  • the floating joined arrangement may also be provided at the radially outer platform.
  • embodiments are conceivable comprising two or more airfoil members which are floatingly connected to a platform member.
  • the floating connection is provided on the same, that is radially inner or outer, end of the airfoil members, but may also be provided on the radially inner end for some of the airfoil members and on the outer end for others.

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

Claims (12)

  1. Unité à palette de guidage à voilure multiple (1) comprenant un premier élément de plate-forme (14), un deuxième élément de plate-forme (15) et au moins deux éléments de voilure (11, 12, 13), les éléments de voilure (11, 12, 13) présentant une extension longitudinale (2) le long d'une envergure de voilure et deux extrémités longitudinales, tous les éléments de voilure (11, 12, 13) étant fixés de manière rigide à un élément de plate-forme (14, 15) à une première extrémité longitudinale et au moins un élément de voilure (11, 13) étant fixé de manière rigide aux deux éléments de plate-formes (14, 15) aux deux extrémités longitudinales, caractérisée en ce qu'au moins un des éléments de voilure (12) est relié de manière flottante à un des éléments de voilure (14) à une deuxième extrémité longitudinale (121) et un dispositif d'articulation flottant longitudinalement (123, 141 ; 122, 142) est prévu entre la deuxième extrémité longitudinale (121) de l'élément de voilure (12) et l'élément de plate-forme (14) de façon à permettre un déplacement de l'élément de voilure (12) par rapport audit élément de plate-forme (14) le long de l'extension longitudinale (2) dudit élément de voilure (12).
  2. Unité à palette de guidage à voilure multiple selon la revendication 1, caractérisée en ce que le dispositif d'articulation flottant longitudinalement (123, 141 ; 122, 142) comprend un élément d'articulation mâle (123, 142), disposé à un de la deuxième extrémité longitudinale (121) de l'élément de voilure (12) et de l'élément de plate-forme (14) et un élément d'articulation femelle (141, 122), disposé au niveau de l'autre de la deuxième extrémité longitudinale (121) de l'élément de voilure et de l'élément de plate-forme, l'élément mâle (123, 142) étant logé à l'intérieur de l'élément femelle (141, 122).
  3. Unité à palette de guidage à voilure multiple selon la revendication 2, caractérisée en ce que l'élément d'articulation mâle est conçu comme une section à cheville (123) au niveau de la deuxième extrémité longitudinale (121) de l'élément de voilure (12) et l'élément femelle est une poche (141) disposée dans l'élément de plate-forme (14).
  4. Unité à palette de guidage à voilure multiple selon l'une des revendications 2 ou 3, caractérisée en ce que la surface externe de l'élément d'articulation mâle (123, 142) est une surface réglée parcourue par des lignes parallèles droites.
  5. Unité à palette de guidage à voilure multiple selon l'une des revendications 3 ou 4, caractérisée en ce que la section à cheville (123) présente une section transversale en forme de voilure.
  6. Unité à palette de guidage à voilure multiple selon l'une des revendications 2 à 5, caractérisée en ce que l'élément d'articulation mâle (123, 142) et l'élément d'articulation femelle (122, 141) sont disposés et conçus de façon à former un ajustement avec jeu.
  7. Unité à palette de guidage à voilure multiple selon la revendication 6, caractérisée en ce que l'ajustement avec jeu est fourni par un élément d'ajustement (17) disposé à l'intérieur de l'élément femelle (122, 141), l'élément d'ajustement (17) étant plus particulièrement conçu comme un élément à double moulage ou moulé par injection.
  8. Unité à palette de guidage à voilure multiple selon l'une des revendications 2 à 7, caractérisée en ce qu'une profondeur de l'élément d'articulation femelle (122, 141) est supérieure à une longueur logée de l'élément d'articulation mâle (123, 142), de façon à ce qu'un interstice existe entre le fond de l'élément d'articulation femelle et une pointe de l'élément d'articulation mâle.
  9. Unité à palette de guidage à voilure multiple selon l'une des revendications précédentes, l'unité à palette de guidage comprenant trois éléments de voilure (11, 12, 13), caractérisée en ce que deux éléments de voilure (11, 13) sont fixés de manière rigide à un élément de plate-forme (14, 15) aux deux extrémités longitudinales et un élément de voilure central (12) est fixé de manière rigide à un premier élément de plate-forme (14) et est relié de manière flottante au deuxième élément de plate-forme (15).
  10. Unité à palette de guidage à voilure multiple selon l'une des revendications précédentes, l'unité à palette de guidage comprenant trois éléments de voilure (11, 12, 13), caractérisée en ce qu'une voilure centrale (12) est fixée de manière rigide à un élément de plate-forme (14, 15) aux deux extrémités longitudinales et chacun des deux éléments de voilure externes (11, 13) est fixé de manière rigide à un élément de plate-forme (14, 15) à sa première extrémité et est relié de manière flottante à un élément de plate-forme (14, 15) au niveau de sa deuxième extrémité.
  11. Unité à palette de guidage à voilure multiple selon la revendication 10, caractérisée en ce que les deux éléments de voilure externes (11, 13) sont fixés de manière rigide au premier élément de plate-forme (15) et sont reliés de manière flottante au deuxième élément de plate-forme (15).
  12. Unité à palette de guidage à voilure multiple selon la revendication 10, caractérisée en ce qu'un premier élément de voilure externe (11) est fixé de manière rigide au premier élément de plate-forme (14) et est relié de manière flottante au deuxième élément de plate-forme (15) et un deuxième élément de voilure (13) est fixé de manière rigide au deuxième élément de plate-forme (15) et est relié de manière flottante au premier élément de plate-forme (14).
EP15161814.7A 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples Not-in-force EP3075960B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP15161814.7A EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples
US15/084,145 US20160290146A1 (en) 2015-03-31 2016-03-29 Multi-airfoil guide vane unit
KR1020160038340A KR20160117330A (ko) 2015-03-31 2016-03-30 다중-에어포일 가이드 베인 유닛
JP2016070822A JP2016194300A (ja) 2015-03-31 2016-03-31 マルチ型翼ガイドベーンユニット
CN201610194226.9A CN106014495A (zh) 2015-03-31 2016-03-31 多翼型件引导叶片单元

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15161814.7A EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples

Publications (2)

Publication Number Publication Date
EP3075960A1 EP3075960A1 (fr) 2016-10-05
EP3075960B1 true EP3075960B1 (fr) 2017-12-27

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Family Applications (1)

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EP15161814.7A Not-in-force EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples

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US (1) US20160290146A1 (fr)
EP (1) EP3075960B1 (fr)
JP (1) JP2016194300A (fr)
KR (1) KR20160117330A (fr)
CN (1) CN106014495A (fr)

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US10767496B2 (en) 2018-03-23 2020-09-08 Rolls-Royce North American Technologies Inc. Turbine blade assembly with mounted platform
US10890081B2 (en) * 2018-04-23 2021-01-12 Rolls-Royce Corporation Turbine disk with platforms coupled to disk
US11466580B2 (en) 2018-05-02 2022-10-11 General Electric Company CMC nozzle with interlocking mechanical joint and fabrication
CN112975188B (zh) * 2021-03-18 2022-08-16 中国科学院工程热物理研究所 燃气轮机压气机静子三联叶片焊接装置
FR3145187A1 (fr) * 2023-01-24 2024-07-26 Safran Aircraft Engines Carter de turbomachine

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US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US5634768A (en) * 1994-11-15 1997-06-03 Solar Turbines Incorporated Airfoil nozzle and shroud assembly
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US6354797B1 (en) 2000-07-27 2002-03-12 General Electric Company Brazeless fillet turbine nozzle
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ATE548542T1 (de) * 2008-12-24 2012-03-15 Techspace Aero Sa Leitschaufelstufe eines verdichters, entsprechender verdichter und verfahren zur sicherung von schaufeln in einer solchen leitschaufelstufe
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Publication number Publication date
JP2016194300A (ja) 2016-11-17
KR20160117330A (ko) 2016-10-10
US20160290146A1 (en) 2016-10-06
EP3075960A1 (fr) 2016-10-05
CN106014495A (zh) 2016-10-12

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