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EP3048256A1 - Rotor comportant une aube de turbine avec un dispositif de verrouillage - Google Patents

Rotor comportant une aube de turbine avec un dispositif de verrouillage Download PDF

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Publication number
EP3048256A1
EP3048256A1 EP15151806.5A EP15151806A EP3048256A1 EP 3048256 A1 EP3048256 A1 EP 3048256A1 EP 15151806 A EP15151806 A EP 15151806A EP 3048256 A1 EP3048256 A1 EP 3048256A1
Authority
EP
European Patent Office
Prior art keywords
rotor
recess
turbine blade
holding piece
blade root
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.)
Withdrawn
Application number
EP15151806.5A
Other languages
German (de)
English (en)
Inventor
Andreas Rehnsch
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP15151806.5A priority Critical patent/EP3048256A1/fr
Priority to EP16700042.1A priority patent/EP3212895B1/fr
Priority to PCT/EP2016/050066 priority patent/WO2016116285A1/fr
Priority to CN201680006607.8A priority patent/CN107208490B/zh
Priority to RU2017129253A priority patent/RU2668512C1/ru
Priority to US15/542,510 priority patent/US10487674B2/en
Priority to KR1020177023020A priority patent/KR101942209B1/ko
Priority to JP2017555832A priority patent/JP6527959B2/ja
Publication of EP3048256A1 publication Critical patent/EP3048256A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • F01D11/005—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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

Definitions

  • the invention relates to a rotor comprising at least one turbine blade and a securing device for axial and radial securing of the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root is adapted to the blade groove, wherein the securing device has a holding piece , which is arranged between the blade groove and the turbine blade root.
  • Blade fasteners are typically used to secure blades to a rotor of a turbomachine, particularly a steam turbine. Due to the comparatively high rotation of the rotor, the rotor blades arranged on the rotor are exposed to high centrifugal forces. The turbine blade root of the turbine blades must therefore withstand high forces and is urged radially outward in the blade groove. In addition to the centrifugal forces, strong vibration loads pose a further problem, which can result in mechanical damage or material fatigue. Corrosion and migration of the blade root by the steaming or vibrations within the blade groove pose further problems. Various solutions such as metal wedges, spring washers or sealing pieces are known for securing the turbine blade root within the blade groove.
  • metal wedges provide locking of the associated blade root within a blade groove both axially and radially, with large blades it is difficult with such metal wedges to produce sufficient holding forces during rotation in the radial direction. Furthermore, metal wedges show a corrosive behavior during prolonged operation in the vapor medium, which makes disassembly difficult.
  • Axially threaded blades are known in turbomachinery, such as steam turbines, which, due to the operating stress, require a design that receives the axial operating forces of the turbine blade and holds the blade in its axial position.
  • Such fuses are also referred to as axial fuses.
  • two notches are arranged in such axial fuses, which are formed superimposed to each other.
  • notches of notches often show increased stress and thus have limited applicability in turbomachinery.
  • the invention has for its object to provide a blade attachment in a turbomachine in which over a long period of operation, a precise and firm support of blades, the associated blade holders, is ensured.
  • a rotor comprising at least one turbine blade and a securing device for axial and radial securing of the turbine blade
  • the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root is adapted to the blade groove
  • the securing device A holding piece, which is arranged between the blade groove and the turbine blade root, wherein the holding piece has a projection which is arranged in a recess in the turbine blade root, wherein the projection engages in the recess such that a displacement of the holding piece in the axial direction is prevented
  • the securing means comprises a force spring exerting a radially acting force from the rotor to the turbine blade.
  • a securing device in a space between the rotor and the turbine blade root.
  • This space is preferably arranged in the rotor.
  • the holding piece is integrated directly into the blade root. This is seen in the axial direction optionally pronounced on the leading edge of the blade root or preferably at the trailing edge of the blade root in the radially inner direction. An expression on the leading edge and trailing edge is possible here in the implementation of an axial recess, which further allows the axial insertion of the modified blade.
  • the securing device has a metal sheet which is arranged in a second recess in the holding piece and in a rotor recess, wherein the sheet engages in the second recess and in the rotor recess in such a way that prevents displacement of the sheet in the axial direction is.
  • the sheet is in this case arranged in a rotor recess and in a second recess in the holding piece and thus forms a barrier for the holding piece to be moved in the axial direction can.
  • a force spring is arranged between the blade groove and the holding piece.
  • the force spring is arranged next to the holding piece between the blade groove and the blade root.
  • the blade root has a front edge arranged in the axial direction and a trailing edge arranged opposite the front edge in the axial direction, wherein the retaining piece protrudes from the front edge to the rear edge.
  • a first locking plate is arranged on the front edge and a second locking plate on the trailing edge.
  • a first force spring is arranged on the front edge and a second force spring on the rear edge.
  • An elongated design is usually a relatively simple manufacturing process, which will lead to a cost savings here.
  • the projection has a rectangular cross-section.
  • the projection is designed as a cylinder and engages in a recess formed as a blind hole. This represents an alternative to the elongated shape of the projection.
  • the rotor recess and the second recess are arranged one above the other in the radial direction.
  • FIG. 1 shows a safety device 1.
  • the rotor has a blade groove 4.
  • This blade groove 4 may be a blade groove 4 formed parallel to a rotation axis 5 of the rotor.
  • the blade groove 4 may also be a curved blade groove 4, which is then arranged at a front edge in the axial direction 7.
  • the rotation axis 5 and the axial direction 7 are arranged parallel to each other.
  • the rotor 2 rotates about the rotation axis 5 at a rotational speed.
  • the turbine blade is adapted in the blade groove 4, so that as little clearance as possible arises between the turbine blade root 3 and the blade groove 4. Without safety device 8, the turbine blade could be moved freely in the axial direction 7.
  • the rotor 2 and the turbine blade may be part of a turbomachine, for example a steam turbine.
  • a turbomachine for example a steam turbine.
  • the centrifugal forces are still comparatively low, during transport, no centrifugal forces are present. Thereby, there is the possibility that the turbine blade can shift in the axial direction 7.
  • a safety device 8 From a certain rotational frequency, the centrifugal forces are so great that the turbine blade presses in the blade groove 4 against so-called support flanks 9, thereby obtaining a stable position. From this particular rotational frequency, axial displacement is difficult to achieve.
  • the securing device 8 is a displacement of the turbine blade effectively prevented in the axial 7 and radial directions.
  • the securing device 8 comprises a holding piece 10
  • FIGS. 1 to 5 show a first embodiment of the holding piece 10.
  • the holding piece 10 is disposed between the blade groove 4 and the turbine blade root 3.
  • the holding piece 10 comprises a front side 11, which is arranged on the front edge 6.
  • the holding piece 10 has an upper side 13 and a lower side 14.
  • the upper side 13 is arranged opposite the lower side 14.
  • the upper side 13 abuts an underside of the turbine blade root 3, as shown in FIG FIG. 2 is shown.
  • the front 11 and the front edge 6 are hereby flush.
  • the underside 14 of the holding piece 10 points in the direction of the axis of rotation 5.
  • the holding piece On the upper side 13, the holding piece on a projection 15 which is elongated in a circumferential direction 16 according to a first variant of the invention.
  • the projection 15 has a rectangular cross-section.
  • the projection 15 is formed over the entire top 13 and protrudes into a recess 17 in the turbine blade root 3.
  • the recess 17 is in this case formed complementary to the projection 15. That is, the recess 17 also has an elongated shape and a rectangular cross section.
  • a displacement of the holding piece, when the projection is arranged in the recess 17, in the axial direction 7 is no longer possible, so that a displacement of the holding piece 10 in the axial direction 7 is prevented.
  • the securing device 10 has a metal sheet 19, which engages in a rotor recess 20 and in a second recess 21, so that a displacement of the plate 19 in the axial direction 7 is prevented.
  • the second recess 21 is arranged in the holding piece 10. The sheet 19 is thereby inserted from the side.
  • the sheet 19 is shaped so as to face in the circumferential direction 16.
  • FIG. 2 shows a cross-sectional view of this first variant of the holding piece 10 and the entire safety device 8.
  • Die FIGS. 3 and 4 show a perspective view of the holding piece 10 in its first variant.
  • the FIG. 5 shows the sheet 19, which is formed in a circumferential direction 16.
  • the sheet has a top sheet 22 which projects into the second recess 21.
  • the sheet bottom 23 protrudes into the rotor recess 20th
  • FIGS. 6 to 9 show a second variant of the securing device. 8
  • the difference of the securing device 8 according to the second variant with respect to the securing device 8 of the first variant is that the projection 15 is not elongated, but is designed as a cylinder 24 and projects into a blind hole in the turbine blade root 3.
  • the cylinder 24 in this case has a similar mode of action as the projection 15 according to FIG. 1, namely that displacement in the axial direction 7 is prevented.
  • FIGS. 7 and 8 show a perspective view of the holding piece 10 according to variant 2.
  • FIG. 9 shows the plate 19, which is designed for the variant 2, wherein the sheet 19 according to variant 1 and variant 3 is identical.
  • the sheet 19 is arranged circumferentially in the circumferential direction 16 and is executed here segmented. This means that the sheet 19 consists of individual segments.
  • the sheet 19 is positively arranged in the rotor recess 20 and in the second recess.
  • the plates 19 are inserted via a milled opening of the circumferential groove to a circumferential position and pushed to its final position, after insertion of the last segment, the segments are connected to each other at the pitches by spot welding.
  • the force spring 18 serves to ensure the installation of the turbine blade to the rotor 2 at a standstill, z. B. during transport.
  • the power spring 18 is formed for example as a plate spring. But the spring 18 can also be performed as a clamping piece.
  • FIGS. 10 to 13 show a third variant of the securing device 8.
  • the third variant is characterized in that the holding piece 10 and the force spring 18 are arranged side by side in the axial direction 7. This means that the force spring 18 is arranged directly on the rotor 2 and directly on the turbine blade root 3 and the force is transmitted directly from the rotor 2 to the turbine blade root 3.
  • the holding piece 10 is arranged in the axial direction 7 next to the force spring 18.
  • the holding piece 10 also has a projection 15 and a second recess 21.
  • the projection 15 may be elongated according to the first variant. Likewise, the projection 15 may be formed according to the second variant as a cylinder.
  • the FIG. 10 shows a cross-sectional view of the securing device 8 according to the third variant.
  • the FIGS. 11 and 12 show a perspective view of the holding piece 10. Die FIG. 13 shows a perspective view of the sheet 19th
  • FIGS. 14 and 15 show a fourth variant of the securing device 8.
  • the safety device 8 according to the fourth variant is characterized in that the holding piece 10 is now formed from the front edge 6 of the turbine blade root 3 to the trailing edge of the turbine blade root. This means that the holding piece 10 is arranged completely from the front edge 6 to the trailing edge.
  • the holding piece 10 also has a projection 15 which in a Recess 17 engages.
  • a metal plate 19 is likewise provided, which engages in a second recess 21 and in a rotor recess 20.
  • the force spring 18 is also arranged between the holding piece 10 and the rotor 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15151806.5A 2015-01-20 2015-01-20 Rotor comportant une aube de turbine avec un dispositif de verrouillage Withdrawn EP3048256A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP15151806.5A EP3048256A1 (fr) 2015-01-20 2015-01-20 Rotor comportant une aube de turbine avec un dispositif de verrouillage
EP16700042.1A EP3212895B1 (fr) 2015-01-20 2016-01-05 Rotor comportant une aube de turbine avec un dispositif de verrouillage
PCT/EP2016/050066 WO2016116285A1 (fr) 2015-01-20 2016-01-05 Fixation d'aube avec dispositif de blocage pour aubes de turbine
CN201680006607.8A CN107208490B (zh) 2015-01-20 2016-01-05 具有用于涡轮叶片的锁定装置的叶片固定装置
RU2017129253A RU2668512C1 (ru) 2015-01-20 2016-01-05 Крепление лопаток с предохранительным устройством для лопаток турбины
US15/542,510 US10487674B2 (en) 2015-01-20 2016-01-05 Blade fastening mechanism having a securing device for turbine blades
KR1020177023020A KR101942209B1 (ko) 2015-01-20 2016-01-05 터빈 블레이드용 고정 장치를 갖는 블레이드 체결 기구
JP2017555832A JP6527959B2 (ja) 2015-01-20 2016-01-05 タービンブレードのための固定デバイスを有するブレード締結機構

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15151806.5A EP3048256A1 (fr) 2015-01-20 2015-01-20 Rotor comportant une aube de turbine avec un dispositif de verrouillage

Publications (1)

Publication Number Publication Date
EP3048256A1 true EP3048256A1 (fr) 2016-07-27

Family

ID=52358662

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15151806.5A Withdrawn EP3048256A1 (fr) 2015-01-20 2015-01-20 Rotor comportant une aube de turbine avec un dispositif de verrouillage
EP16700042.1A Active EP3212895B1 (fr) 2015-01-20 2016-01-05 Rotor comportant une aube de turbine avec un dispositif de verrouillage

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16700042.1A Active EP3212895B1 (fr) 2015-01-20 2016-01-05 Rotor comportant une aube de turbine avec un dispositif de verrouillage

Country Status (7)

Country Link
US (1) US10487674B2 (fr)
EP (2) EP3048256A1 (fr)
JP (1) JP6527959B2 (fr)
KR (1) KR101942209B1 (fr)
CN (1) CN107208490B (fr)
RU (1) RU2668512C1 (fr)
WO (1) WO2016116285A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3070423A1 (fr) * 2017-08-22 2019-03-01 Safran Aircraft Engines Attache poignard avec joint et ressort d'une aube de redresseur
US12221899B2 (en) * 2023-06-15 2025-02-11 General Electric Company Methods and apparatuses for blade locking

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201600130088A1 (it) * 2016-12-22 2018-06-22 Nuovo Pignone Tecnologie Srl Pala di turbina e set di fissaggio
KR102236266B1 (ko) 2017-11-17 2021-04-05 한화에어로스페이스 주식회사 회전체
DE102019210647A1 (de) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Schaufelkranz für eine axiale Turbomaschine
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신
US11208903B1 (en) * 2020-11-20 2021-12-28 Solar Turbines Incorporated Stiffness coupling and vibration damping for turbine blade shroud
KR102478172B1 (ko) * 2021-02-02 2022-12-14 두산에너빌리티 주식회사 회전 기계, 이를 포함하는 가스 터빈, 회전 기계의 조립 방법
KR102703146B1 (ko) * 2022-01-14 2024-09-04 두산에너빌리티 주식회사 블레이드 고정 조립체, 이를 포함하는 가스 터빈 및 가스 터빈 제조 방법
KR20240120128A (ko) 2023-01-31 2024-08-07 두산에너빌리티 주식회사 블레이드 고정 조립체 및 이를 포함하는 가스 터빈

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US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
US4668167A (en) * 1985-08-08 1987-05-26 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multifunction labyrinth seal support disk for a turbojet engine rotor
US5431543A (en) * 1994-05-02 1995-07-11 Westinghouse Elec Corp. Turbine blade locking assembly
EP2299060A1 (fr) * 2009-09-17 2011-03-23 Siemens Aktiengesellschaft Fixation des aubes avec dispositif de verrouillage pour aubes de turbines

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US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
JPS6469702A (en) 1987-09-09 1989-03-15 Hitachi Ltd Fixation of movable blade of axial flow rotary machine
JPH01237304A (ja) 1988-03-15 1989-09-21 Toshiba Corp 蒸気タービン動翼押上装置
US5236309A (en) 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
FR2807096B1 (fr) * 2000-03-30 2002-05-31 Abb Alstom Power Nv Disque rotorique de turbine equipe d'ailettes a pied de sapin et procede de montage d'une ailette sur un disque
EP1892380A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Fixation d'aubes de turbine
EP1978211A1 (fr) 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Dispositif de sécurité axiale sur des aubes mobiles d'un moteur tout comme turbine à gaz dotée d'un tel dispositif
JP5692994B2 (ja) * 2009-12-08 2015-04-01 三菱重工業株式会社 動翼固定構造およびこれを備えた回転機械ならびに動翼着脱方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
US4668167A (en) * 1985-08-08 1987-05-26 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multifunction labyrinth seal support disk for a turbojet engine rotor
US5431543A (en) * 1994-05-02 1995-07-11 Westinghouse Elec Corp. Turbine blade locking assembly
EP2299060A1 (fr) * 2009-09-17 2011-03-23 Siemens Aktiengesellschaft Fixation des aubes avec dispositif de verrouillage pour aubes de turbines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3070423A1 (fr) * 2017-08-22 2019-03-01 Safran Aircraft Engines Attache poignard avec joint et ressort d'une aube de redresseur
US12221899B2 (en) * 2023-06-15 2025-02-11 General Electric Company Methods and apparatuses for blade locking

Also Published As

Publication number Publication date
EP3212895B1 (fr) 2021-03-17
EP3212895A1 (fr) 2017-09-06
KR101942209B1 (ko) 2019-01-24
KR20170103010A (ko) 2017-09-12
JP6527959B2 (ja) 2019-06-12
JP2018505994A (ja) 2018-03-01
CN107208490B (zh) 2019-08-06
US20180266259A1 (en) 2018-09-20
US10487674B2 (en) 2019-11-26
RU2668512C1 (ru) 2018-10-01
WO2016116285A1 (fr) 2016-07-28
CN107208490A (zh) 2017-09-26

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