EP3788236B1 - Rotor pourvu d'une pièce disposée entre deux disques de rotor - Google Patents

Rotor pourvu d'une pièce disposée entre deux disques de rotor Download PDF

Info

Publication number
EP3788236B1
EP3788236B1 EP19752935.7A EP19752935A EP3788236B1 EP 3788236 B1 EP3788236 B1 EP 3788236B1 EP 19752935 A EP19752935 A EP 19752935A EP 3788236 B1 EP3788236 B1 EP 3788236B1
Authority
EP
European Patent Office
Prior art keywords
rotor
annular projection
recesses
radially
retaining grooves
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
EP19752935.7A
Other languages
German (de)
English (en)
Other versions
EP3788236A1 (fr
Inventor
Peter Kury
Harald Hoell
Karsten Kolk
Vyacheslav Veitsman
Yulia Bagaeva
Christopher W. Ross
Peter Schröder
Andrew R. Waddell
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Publication of EP3788236A1 publication Critical patent/EP3788236A1/fr
Application granted granted Critical
Publication of EP3788236B1 publication Critical patent/EP3788236B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a rotor of a gas turbine, which has at least two rotor disks connected to one another, between which an annular rotor component is arranged.
  • annular rotor component for shielding the inner region of the rotor from the hot gas flowing through the gas turbine being arranged between the rotor disks.
  • the two rotor disks each have a plurality of rotor blades distributed on the outer circumference. Between the two rows of rotor blades there is a row with guide vanes distributed around the circumference, each of which is fastened to the stationary housing. Due to the rotation of the rotor, there is inevitably a gap between the guide vanes and the moving vanes. In principle, this made it possible for hot gas to enter the area radially inside the guide vanes.
  • an annular rotor component is arranged between the two adjacent rotor disks in order to keep the hot gas away from the interior of the rotor. For this purpose, this rotor component is mounted on both sides of the rotor disk.
  • the only task of the rotor component is to prevent hot gas from penetrating. Another function is usually not available. Accordingly, the mounting of the rotor component is kept simple in the usual way, with only one annular, axially extending shoulder engaging in a corresponding annular groove.
  • Unintentional rotation of the rotor component relative to the rotor disks is generally prevented in that there is an interference fit between the rotor component and one of the rotor disks in at least one location in the engagement of the annular shoulder in the annular groove.
  • two adjacent rotor disks each have an opposite annular, axially extending projection.
  • a rotor component for sealing the area between the two rotor disks is arranged between the rotor disks. This has a circumferential shoulder at each of the two axial ends, which rests against a projection of the corresponding rotor disk on the side pointing towards the rotor axis.
  • a projection In order to prevent a relative displacement of the rotor component relative to the rotor disks, provision is made in this case for a projection to have recesses into which engaging shoulders of the rotor component engage.
  • the object of the present invention is therefore to provide a rotor component by means of which the area between two rotor disks can be advantageously sealed and the blade retaining grooves of a rotor disk can be covered at least in sections.
  • the generic rotor is initially used in a gas turbine. Irrespective of this, however, it is also possible to use the embodiment of the rotor in another turbomachine, for example in a steam turbine.
  • At least the rotor has a first rotor disk and a second rotor disk which is directly and firmly connected to the first rotor disk.
  • the rotor disks each have a plurality of blade retaining grooves distributed on the outer circumference and penetrating the respective rotor disk axially. The blade retaining grooves are used here to hold moving blades.
  • first rotor disk has a peripheral radially below the blade retaining grooves, extending axially to the second Rotor disc towards extending first annular projection.
  • second rotor disk radially below the blade retaining grooves has a circumferential second annular projection that extends axially toward the first rotor disk.
  • An annular rotor component is arranged between the two rotor disks in the region of the blade retaining grooves and/or radially below the blade retaining grooves. This encloses sections of the rotor located within the rotor component, or sections of the two rotor disks.
  • the rotor component has a circumferential support section on each of its two axial ends. The first support section is located below the first annular projection on the side facing the rotor axis, and the second support section is located radially below the second annular projection. Provision can be made for the respective support section to rest against the annular projection with a press fit or leave a slight gap to the annular projection—while ensuring centering.
  • a coupling between the rotor component of the first rotor disk is produced radially outside of the annular projection, which coupling prevents relative displacement in the circumferential direction.
  • the first rotor disk has at least two first recesses distributed around the circumference.
  • the rotor component has complementary second engagement shoulders, which each engage in a corresponding first recess.
  • the first rotor disk has at least two first engagement shoulders distributed around the circumference.
  • the rotor component has complementary second recesses, so that the first engagement sections engage in the second recesses.
  • This embodiment brings about a reliable coupling between the rotor component and the rotor disks, so that a relative movement is prevented even if a press fit is lost. In this respect, no friction can occur between the components and negatively affect the service life.
  • the rotor component also has at least one circumferential, radially extending disk section. This is arranged at an axial end and can partially cover the rotor disk and the blade retaining grooves.
  • An advantageous stabilization of the rotor component, in particular the disk section, and an advantageous securing of the connection between the rotor component and the rotor disks is achieved according to the invention by the disk section having a first area with a first material thickness in the axial direction and radially outside the first area a second area with an increased material thickness and has at least twice the material thickness.
  • the rotor component has at one axial end an axially opening first annular groove enclosing the first annular projection and opposite at the other axial end an axially opening second annular groove enclosing the second annular projection.
  • the flanks of the respective ring groove located on the side pointing towards the rotor axis are formed by the support sections.
  • the centering of the rotor component relative to the rotor disks under the various operating states can be improved if a radially outer flank of the first annular groove or a radially outer flank of the first annular groove rests against the first annular projection Flank of the second annular groove rests against the second annular projection.
  • the first recesses in the first rotor disk and/or the second recesses in the rotor component can be realized in different ways.
  • the first rotor disk or the rotor component has a peripheral annular shoulder for this purpose.
  • the recess interrupts the peripheral ring shoulder.
  • the recess is delimited on both sides by projections which extend in sections in the circumferential direction.
  • an engaging shoulder is arranged on both sides of a respective recess.
  • a first engagement shoulder of the first rotor disk engages in a second recess of the rotor component and a second engagement shoulder of the rotor component engages in a first recess of the first rotor disk, mutually adjacent in the circumferential direction.
  • first engagement sections in the first rotor disk are each positioned centrally between two blade retaining grooves. Accordingly, it is advantageous if the first recesses are each arranged as an extension of the blade retaining grooves.
  • these advantageously have a length in the circumferential direction that is less than the smallest distance between two blade retaining grooves.
  • connection is placed immediately above the annular projection.
  • the first rotor disk has the first engagement shoulders on the radially outward-facing side of the annular projection.
  • the second recesses in the rotor component are complementary to this necessary.
  • the rotor component advantageously has a first annular groove in which the first annular projection engages. Consequently, the recess is to be arranged on the radially outer flank of the annular groove.
  • the first engagement shoulder and thus the second recess is preferably to be arranged at a distance from the axially free end of the annular projection. This avoids additional loading by the second recess in the area of the groove base of the first annular groove.
  • the engagement heels can be realized in different ways.
  • a reliable connection with the engagement shoulders is created when they are formed in one piece with the first rotor disk and in one piece with the rotor component.
  • a thickened area is advantageously arranged on the side pointing away from the directly adjacent, ground-breaking side in order to form the second region.
  • the arrangement of the second recesses and/or the second engagement shoulders on the rotor component takes place in a particularly advantageous manner in the second area of the disc section.
  • a rotor in a first exemplary embodiment is sketched in longitudinal section only in the area of the rotor component 11 .
  • the further design of the rotor can be selected using conventional embodiments.
  • the rotor has at least a first rotor disk 01 and a second rotor disk 06.
  • a circumferential, axially extending ring projection 03, 08 is arranged on each of these 01, 06.
  • the rotor component 11 Between the rotor disks 01, 06 is the rotor component 11, which 11 has a circumferential annular groove 12, 17 for attachment to the rotor disks 01, 06, with the first annular projection 03 in the first annular groove 12 and the second annular projection 08 in the second annular groove 17 intervenes.
  • a support section 13, 18 formed by the rotor component 11 is located radially below the respective annular projection 03, 08. These 13, 18 are supported on the respective annular projection 03, 08, at least in the event of centrifugal force.
  • the rotor component 11 has a circumferential, radially extending disk section 20 .
  • the coupling between the rotor component 11 and the first rotor disk 01 is located in the radially outer area.
  • first rotor disk 01 in a perspective view.
  • Circumferential ring projection 03 can be seen, as well as blade retaining grooves 02 that penetrate axially through first rotor disk 01 radially outside.
  • first engagement step 05 Between each two blade retaining grooves 02 is a first engagement step 05.
  • first engagement sections 05 there is a corresponding first recess.
  • the 3 12 shows the rotor component 11 which is complementary thereto.
  • the circumferential annular grooves 12, 17 can again be seen, with those arranged on the side pointing towards the rotor axis Support sections 13, 18.
  • the disk section 20, which extends radially at one axial end directly adjacent to the first rotor disk 01, is divided into a radially inner first area and a radially outer second area, with the second area having a cover 19 and thus at least twice the material thickness of the first area reached.
  • the second engagement projections 15 arranged on the rotor component 11 and the second recesses 14 in between are arranged opposite the cover 19 in the radially outer area.
  • Analog of the 1 show the 4 a rotor in a second exemplary embodiment.
  • the rotor has a first rotor disk 21 and a second rotor disk 26 .
  • a circumferential, axially extending ring projection 23, 28 is arranged.
  • the rotor component 31 is located between the rotor disks 21, 26 and has a circumferential annular groove 32, 37 in each case for attachment to the rotor disks 21, 26.
  • the rotor component 31 has a circumferential, radially extending disc section 40 .
  • the coupling between the rotor component 31 and the first rotor disk 21 is located immediately radially outside of the first annular projection 23.
  • the figure 5 shows the rotor component 31 in a perspective view.
  • the circumferential first annular groove 32 with the support sections arranged on the side pointing towards the rotor axis can again be seen.
  • the at one axial end immediately adjacent to the second rotor disk 26 radially extending Disk section 40 is analogous to that stated above.
  • the rotor component In contrast to the previous embodiment, provision is made in this case for the rotor component to have a peripheral annular shoulder 35 on the radially outer flank of the first annular groove 32 on the side facing the rotor axis. This 35 is interrupted several times by second recesses 34 distributed around the circumference.
  • the 6 shows the first rotor disk 21 in a perspective view.
  • the circumferential annular projection 23 and the blade retaining grooves 02 can be seen.
  • the first rotor disk 21 has the first engagement shoulders 25, which are complementary to the second recesses 34, on the radially outer side on the first annular projection 23.

Landscapes

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

Claims (9)

  1. Rotor, en particulier d'une turbine à gaz,
    comprenant un premier disque (01, 21) de rotor, qui (01, 21) a, réparties sur le pourtour, un nombre d'encoches (02, 22) de retenue d'aube traversant axialement le premier disque (01, 21) du rotor pour la réception d'aubes mobiles et, radialement en-dessous des encoches (02, 22) de retenue d'aube, une première saillie (03, 23) annulaire faisant le tour en s'étendant axialement, et
    comprenant un deuxième disque (06, 26) de rotor fixé au premier disque (01, 21) du rotor, qui (06, 26) a, réparties sur le pourtour, une pluralité d'encoches de retenue d'aube, traversant axialement le deuxième disque (06, 26) du rotor pour la réception d'aubes mobiles et, radialement en-dessous des encoches de retenue d'aube, une deuxième saillie (08, 28) annulaire faisant le tour en s'étendant axialement par rapport à la première saillie (03, 23) annulaire, et
    comprenant une pièce (11, 31) de rotor, qui (11, 31) fait le tour, qui est disposée entre les disques (01, 06, 21, 26) du rotor, et qui a une première partie (13) d'appui venant, du côté tourné vers l'axe du rotor, en contact avec la première saillie (03, 23) annulaire, et une deuxième partie (18) d'appui venant, du côté tourné vers l'axe du rotor, en contact avec la deuxième saillie (08, 28) annulaire ;
    dans lequel le premier disque (01) du rotor a, à l'extérieur radialement et/ou du côté tourné vers l'extérieur radialement de la première saillie (03) annulaire, au moins deux premiers évidements répartis sur le pourtour et la pièce (11) de rotor a des deuxièmes ressauts (15) de pénétration pénétrant respectivement dans les premiers évidements ; et/ou
    dans lequel la pièce (11, 31) du rotor a, radialement à l'extérieur et/ou du côté tourné vers l'extérieur radialement de la première saillie (03, 23) annulaire, au moins deux deuxièmes évidements (14, 34) répartis sur le pourtour et le premier disque (01, 21) du rotor a des premiers ressauts (05, 25) de pénétration pénétrant respectivement dans les deuxièmes évidements (14, 34), caractérisé en ce que
    la pièce (11, 31) du rotor a, à au moins une extrémité axiale, une partie (20, 40) de disque, qui s'étend radialement et qui (20, 40) recouvre les encoches (02, 22) de retenue d'aube d'un disque (01, 26) du rotor, au moins par endroits, et une première région ayant une première épaisseur de matériau et, radialement à l'extérieur de la première région, une deuxième région ayant une épaisseur de matériau d'au moins 2 fois par rapport à la première épaisseur de matériau.
  2. Rotor suivant la revendication 1,
    caractérisé
    en ce que la pièce (11, 31) du rotor a une première encoche (12, 32) annulaire s'ouvrant axialement et entourant la première saillie (03, 23) annulaire et/ou une deuxième encoche (17, 37) annulaire s'ouvrant axialement et entourant la deuxième saillie (08, 28) annulaire.
  3. Rotor suivant la revendication 2,
    caractérisé
    en ce qu'un flanc extérieur radialement de la première encoche (12, 32) annulaire s'applique à la première saillie (03, 23) annulaire et/ou un flanc extérieur radialement de la deuxième encoche (17, 37) annulaire s'applique à la deuxième saillie (08, 28) annulaire.
  4. Rotor suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que, des deux côtés des évidements, sont disposées des saillies s'étendant axialement et par endroits dans la direction du pourtour ; et/ou
    en ce que les évidements (34) sont disposés dans un ressaut (35) annulaire faisant le tour.
  5. Rotor suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que, sur le premier disque (01) du rotor, les premiers ressauts (05) de pénétration sont disposés respectivement dans une direction du pourtour entre deux encoches (02) de retenue d'aube ; et/ou
    en ce que, sur le premier disque (01) du rotor, les premiers évidements sont disposés respectivement en prolongement des encoches (02) de retenue d'aube.
  6. Rotor suivant la revendication 5,
    caractérisé
    en ce que la longueur des premiers ressauts (05) de pénétration est, dans la direction du pourtour, respectivement inférieure ou égale à la distance la plus petite entre deux encoches (02) de retenue d'aube.
  7. Rotor suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que, sur le premier disque (21) du rotor, les premiers ressauts (25) de pénétration sont disposés, du côté tourné vers l'extérieur radialement de la saillie (23) annulaire, à distance de l'extrémité libre axialement de la saillie (23) annulaire.
  8. Rotor suivant l'une des revendications 1 à 7,
    caractérisé
    en ce que la deuxième région est formée par un épaississement (19), du côté non tourné vers le disque (01, 26) du rotor immédiatement voisin.
  9. Rotor suivant la revendication 8,
    caractérisé
    en ce que les ressauts (15) de pénétration et/ou les évidements (14) sont disposés dans la deuxième région.
EP19752935.7A 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor Active EP3788236B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201862713572P 2018-08-02 2018-08-02
PCT/EP2019/069866 WO2020025406A1 (fr) 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor

Publications (2)

Publication Number Publication Date
EP3788236A1 EP3788236A1 (fr) 2021-03-10
EP3788236B1 true EP3788236B1 (fr) 2023-06-21

Family

ID=67620379

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19752935.7A Active EP3788236B1 (fr) 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor

Country Status (6)

Country Link
US (1) US11339662B2 (fr)
EP (1) EP3788236B1 (fr)
JP (1) JP7092938B2 (fr)
KR (1) KR102537955B1 (fr)
CN (1) CN112534119B (fr)
WO (1) WO2020025406A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240084708A1 (en) * 2016-02-05 2024-03-14 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs

Family Cites Families (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
GB802476A (en) 1955-09-29 1958-10-08 Rolls Royce Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines
US3343806A (en) * 1965-05-27 1967-09-26 Gen Electric Rotor assembly for gas turbine engines
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
US4645424A (en) * 1984-07-23 1987-02-24 United Technologies Corporation Rotating seal for gas turbine engine
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
US4669959A (en) * 1984-07-23 1987-06-02 United Technologies Corporation Breach lock anti-rotation key
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
US4664599A (en) * 1985-05-01 1987-05-12 United Technologies Corporation Two stage turbine rotor assembly
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
DE69305326T2 (de) * 1992-02-10 1997-05-07 United Technologies Corp Ejektor für kühlfluid
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
US5338154A (en) * 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
JPH07139305A (ja) * 1993-11-16 1995-05-30 Mitsubishi Heavy Ind Ltd ラビリンスシール固定構造
JPH07324632A (ja) * 1994-05-30 1995-12-12 Mitsubishi Heavy Ind Ltd ガスタービン動翼の冷却空気シール装置
DE19940525A1 (de) 1999-08-26 2001-03-01 Asea Brown Boveri Wärmestaueinheit für eine Rotoranordnung
US6190131B1 (en) * 1999-08-31 2001-02-20 General Electric Co. Non-integral balanced coverplate and coverplate centering slot for a turbine
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
US6769865B2 (en) * 2002-03-22 2004-08-03 General Electric Company Band cooled turbine nozzle
US6899520B2 (en) * 2003-09-02 2005-05-31 General Electric Company Methods and apparatus to reduce seal rubbing within gas turbine engines
CN101258305B (zh) * 2005-09-07 2011-06-15 西门子公司 用于对转子中的动叶片进行轴向固定的装置、用于一种这样的装置的密封件以及一种这样的装置的应用
US7500832B2 (en) * 2006-07-06 2009-03-10 Siemens Energy, Inc. Turbine blade self locking seal plate system
PL1944471T3 (pl) * 2007-01-09 2010-02-26 Siemens Ag Osiowy segment wirnika dla wirnika turbiny
EP2025867A1 (fr) * 2007-08-10 2009-02-18 Siemens Aktiengesellschaft Rotor pour une turbomachine
US8221062B2 (en) * 2009-01-14 2012-07-17 General Electric Company Device and system for reducing secondary air flow in a gas turbine
US8206119B2 (en) * 2009-02-05 2012-06-26 General Electric Company Turbine coverplate systems
EP2239419A1 (fr) * 2009-03-31 2010-10-13 Siemens Aktiengesellschaft Rotor de turbomachine axiale doté d'un disque d'étanchéité
US8608436B2 (en) * 2010-08-31 2013-12-17 General Electric Company Tapered collet connection of rotor components
US9404376B2 (en) 2013-10-28 2016-08-02 General Electric Company Sealing component for reducing secondary airflow in a turbine system
EP2873807A1 (fr) * 2013-11-18 2015-05-20 Siemens Aktiengesellschaft Plaque de recouvrement, aube mobile, disque de roue, boulon et turbine à gaz
GB201417039D0 (en) * 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
GB201417038D0 (en) * 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement
GB201504725D0 (en) * 2015-03-20 2015-05-06 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US10724375B2 (en) * 2016-02-12 2020-07-28 General Electric Company Gas turbine engine with ring damper
GB201604473D0 (en) * 2016-03-16 2016-04-27 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US10196916B2 (en) * 2016-04-08 2019-02-05 Siemens Aktiengesellschaft Rotor disk having an end-side sealing element
EP3287595A1 (fr) * 2016-08-25 2018-02-28 Siemens Aktiengesellschaft Rotor dote d'un anneau d'etancheite segmente
EP3318724A1 (fr) * 2016-11-04 2018-05-09 Siemens Aktiengesellschaft Segment d'étanchéité d'un rotor et rotor
US10557356B2 (en) * 2016-11-15 2020-02-11 General Electric Company Combined balance weight and anti-rotation key
US10920598B2 (en) * 2017-05-02 2021-02-16 Rolls-Royce Corporation Rotor assembly cover plate

Also Published As

Publication number Publication date
US11339662B2 (en) 2022-05-24
CN112534119A (zh) 2021-03-19
JP7092938B2 (ja) 2022-06-28
EP3788236A1 (fr) 2021-03-10
KR20210031984A (ko) 2021-03-23
US20210310359A1 (en) 2021-10-07
CN112534119B (zh) 2023-04-14
KR102537955B1 (ko) 2023-05-31
WO2020025406A1 (fr) 2020-02-06
JP2021533304A (ja) 2021-12-02

Similar Documents

Publication Publication Date Title
EP2399004B1 (fr) Section de rotor pour un rotor d'une turbomachine, aube rotorique pour une turbomachine et élément de blocage
EP1922471A1 (fr) Systeme de retenue axiale de d'aubes mobiles dans un rotor et utilisation dudit systeme
EP1148209B1 (fr) Configuration de joint inter-étages
EP2875264B1 (fr) Ensemble pourvu d'un joint étanche à gaz
DE102015116935A1 (de) Sicherungsvorrichtung zur axialen Sicherung einer Laufschaufel und Rotorvorrichtung mit einer derartigen Sicherungsvorrichtung
EP2129871A1 (fr) Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement
DE102010027762B4 (de) Einsatzstück für eine Strömungsmaschine und damit ausgerüstete Strömungsmaschine
EP2464831B1 (fr) Éléments de fixation d'aubes directrices dans une turbomachine
EP3788236B1 (fr) Rotor pourvu d'une pièce disposée entre deux disques de rotor
EP1524409B1 (fr) Dispositif de verrouillage d'aube
DE4416320A1 (de) Axialwinkelscheibe
EP3695100B1 (fr) Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP3724456B1 (fr) Rotor à surfaces de contact optimisées au niveau de forces centrifuges
EP3885535B1 (fr) Bague d'étanchéité pour un rotor et rotor doté d'une telle bague d'étanchéité
WO2008116651A1 (fr) Élément d'écartement et dispositif de freinage
EP3350416B1 (fr) Turbine à gaz munie d'un support amélioré du carter intérieur
EP3613952A1 (fr) Dispositif d'aube directrice réglable, aube directrice, porte-joint et turbomachine
EP3064705B1 (fr) Rotor doté d'une tôle de sûreté destiné à protéger un verrouillage rotatif contre le dévissage
EP3561234B1 (fr) Rotor pourvu de dispositif d'étanchéité
EP3348786A1 (fr) Rotor comprenant une couverture de conduite et plaques d'étanchéité
EP3511524A1 (fr) Rotor doté des éléments d'étanchéité montés au niveau des rainures de maintien de l'aube de rotor
DE102019101958A1 (de) Kupplungsbetätigungseinrichtung und Kupplungseinrichtung
EP3581765A1 (fr) Rotor pourvu de pales tournantes verrouillées axialement sur le disque de rotor
DE102019210753A1 (de) Integral beschaufelter Turbomaschinen Rotor
DE416502C (de) Nachgiebige Befestigung von Turbinenradscheiben auf der Welle

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20201204

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20230118

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502019008277

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1581035

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230621

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230921

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230920

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230922

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230725

Year of fee payment: 5

Ref country code: DE

Payment date: 20230726

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231023

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231021

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20230731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230724

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502019008277

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230724

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230621

26N No opposition filed

Effective date: 20240322

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20230921