EP2183467B1 - Agencement de rotor de turbine - Google Patents

Agencement de rotor de turbine Download PDF

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Publication number
EP2183467B1
EP2183467B1 EP08775236.6A EP08775236A EP2183467B1 EP 2183467 B1 EP2183467 B1 EP 2183467B1 EP 08775236 A EP08775236 A EP 08775236A EP 2183467 B1 EP2183467 B1 EP 2183467B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
blades
recesses
rotor according
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
EP08775236.6A
Other languages
German (de)
English (en)
Other versions
EP2183467A1 (fr
EP2183467B2 (fr
Inventor
Helmar Wunderle
Stefan Schlechtriem
Peter Graf
Silvio Glaser
Beat Von Arx
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
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2183467A1 publication Critical patent/EP2183467A1/fr
Publication of EP2183467B1 publication Critical patent/EP2183467B1/fr
Application granted granted Critical
Publication of EP2183467B2 publication Critical patent/EP2183467B2/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
    • 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
    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the present invention relates to a rotor for a turbomachine according to the preamble of claim 1.
  • the individual blades are fixed to a rotor in a ring by the rotor has on its outer periphery via a plurality of axially and parallel circumferentially juxtaposed recesses, which are formed for example as a die of a Christmas tree profile.
  • the blades reaching for installation have a form-fitting corresponding blade root, which is designed as a corresponding male part of the Christmas tree profile with respect to the corresponding matrices in the rotor.
  • the blades are successively inserted in the axial direction in these recesses of the rotor, and for sealing between the adjacent blades push while the lower shrouds of the adjacent blades side by side.
  • the WO 03/027445 has become known, it is to take into account the fact that on the one hand between the adjacent shrouds at all times the best possible seal must be present, but on the other hand, that the thermal expansion of the individual components must be considered.
  • a rim 814) is provided with a neck (12) interposed intermediately with respect to the rotor.
  • the rim allows the inclusion of the blade (44).
  • the seal of the inserted blade is to be accomplished between the upper-side contour of the rim and the underside course of the foot cover plate of the blade. Accordingly, it must be used for receiving and sealing the blade on an intermediate element, the seal is then to be achieved exclusively by the merger of two flat surfaces. Sonach here is no labyrinth seal given.
  • Out GB 1 527 074 shows that the individual rotors each have a rotor disk 15, on the outer circumference of a plurality of each substantially axially extending slots is arranged, in which the blade roots 16 of the rotor blades 17 are held.
  • the rotor disk 15 is surrounded by a cage-like ring whose cage shape is formed by end-face rings 19 and by cage bars 20 extending in the axial direction.
  • the cage bars 20 are located radially inside the blade root ring plates 18.
  • the ring parts 19 held together by the cage bars 20 are in the form of radial flanges 21, 22.
  • the reference stop between the rotor 15 and the blade 17 is formed on the one hand by a shoulder in the blade ring plate 18 and on the other hand by ring part 19 , wherein ring member 19 is part of a radial flange 22, which in turn is part of a Cage shape is; this cage shape is placed in the radial direction of the rotor disk 15.
  • the reference stop is therefore not formed directly between the blade root profile and the shroud of the blade.
  • the invention is therefore inter alia the object of providing a simple rotor assembly for improving the seal on constructions of rotors of the type mentioned above.
  • it is therefore about to propose such an improved rotor assembly for a rotor having a plurality of anchored in the rotor, arranged in the form of a rotating ring blades.
  • the rotor has a plurality of substantially axially extending, profiled with a profiled recesses into which a ring of blades, which have corresponding with the profile blade root profiles, in a substantially axial insertion direction are preferably inserted positively and / or non-positively ,
  • the rotor between the recesses over extending in the axial direction and circumferential direction tangential surface portions or peripheral surface portions, which are covered by lower shrouds of circumferentially adjacent blades arranged in the radial direction substantially at least indirectly.
  • the core of the invention thus consists, to some extent in the sense of a labyrinth seal, of improving the seal between rotor and blade or shroud of the blade. As a side effect, this results in a clever arrangement of gradations that the blade is pushed when pushed against a stop. In other words, the right axial position for the fixation is specified by the gradation.
  • a first preferred embodiment of the rotor assembly is characterized in that the steps are provided on all circumferentially arranged peripheral surface portions of the rotor and corresponding recesses are provided on all the blades.
  • the steps are provided on all circumferentially arranged peripheral surface portions of the rotor and corresponding recesses are provided on all the blades.
  • the gradations are arranged on one of the insertion side opposite stop side of the rotor and are preferably flush with this stop side.
  • the gradations are as Ring sections on the peripheral surface portions with an axial section rectangular or square cross-section (but other shapes such as triangle, trapezoid or corresponding rounded shapes are possible) is formed.
  • the steps are advantageously formed over less than 50% of the axial extent of the peripheral surface portions, preferably over less than 20%, more preferably over less than 10% of the axial extent of the peripheral surface portions.
  • the steps are formed with a radial height, which serves in each case the final purpose and is dependent on the respective designed gradations.
  • the gradations and the recesses are advantageously made flush (in the axial and in the radial direction), optionally optionally in the edge region or over the entire grading sealant can be arranged or a profiling is made, although the one purpose fulfilled, but also pursued in the particular desired tightness.
  • the present invention relates to a blade, in particular for use in a rotor assembly, as described above.
  • the blade is preferably characterized in that it has an airfoil and a blade root formed thereon, wherein the blade root has a blade root profile and a lower shroud, and on the underside of the shroud there is a recess open in the direction of insertion and towards the rotor, wherein the Recess preferably extends over the entire tangential respectively circumferential width of the underside of the shroud on both sides of the airfoil.
  • the blade root profile is designed as a dovetail profile or as a Christmas tree profile.
  • the present invention relates to a rotor, in particular for Use as a rotor assembly as described above, and preferably for common use with a bucket as described above.
  • the rotor is preferably characterized in that it is designed for anchoring a circumferential ring of blades, for which the rotor has a plurality of substantially axially extending, profiled recesses, in which the ring of blades, which have corresponding blade root profiles in one substantially axial insertion direction in these recesses preferably positive and / or non-positively inserted, and wherein the rotor between the recesses extending in the axial direction and circumferential direction tangential surface portions or peripheral surface sections, which of lower shrouds of circumferentially adjacent arranged blades in the radial direction be substantially covered at least indirectly.
  • at least one of the tangential surface sections respectively peripheral surface sections is provided with a gradation in the radial direction.
  • the profiled recesses are designed as dovetail profiles or
  • FIG. 1 First, a structure of a rotor according to the prior art is shown.
  • the rotor 1 comprises a central part, which has a peripheral surface substantially in the form of a cylindrical surface.
  • a recesses 4 are formed.
  • the recesses are designed as Christmas tree profiles.
  • the recesses 4 extend in the radial direction R inwardly to the axis of the rotor.
  • the Tannenbaumprofile each have alternately arranged grooves 10 and ribs 11, which are arranged in the axial direction.
  • the recesses 4 are used for axially receiving the blades 2, which are formed with a corresponding male profile on the blade root.
  • the recesses 4 are uniformly distributed around the circumference of the rotor 1, and between the individual recesses 4 remain portions of the substantially cylindrical peripheral surface. These peripheral surface portions 5 are, when the blades 2 are inserted, usually covered by the blade root 3, or specifically from the lower shroud 7 of the blade. 2
  • the peripheral surface is divided into two circumferential surface sections 5 and 5 ', respectively.
  • the sections 5, 5 ' can either actually be formed as curved sections of a cylinder surface, but they can also be designed in each case as tangential planes, wherein 5 and 5' can be arranged in the same plane or can be tilted relative to each other.
  • FIG. 1b the process of inserting a blade is shown schematically. This in a section in the plane of the axis of the rotor, that is, in a radial direction.
  • a blade 2 comprises an airfoil 9, which optionally may additionally have a shroud on the radially outer side (not shown in this figure).
  • the blade root 3 formed on the lower side comprises, on the one hand, a lower shroud 7 and, on the radial side, it is integrally formed downward over the blade root profile 16.
  • the blade root profile 16 corresponds to a certain extent a negative of the recesses 4, that is, it is also formed as a corresponding Christmas tree profile.
  • the Christmas tree profile of the blade root profile 16 corresponds as closely as possible to the Christmas tree profile of the recesses 4 in order to ensure a full seat of 16 in FIG.
  • the blade is inserted in an axial direction A in the recesses 4 in the insertion direction 8, wherein the lower shroud usually rests substantially flush with the peripheral surface portions 5.
  • FIG. 2 Now, a modification according to the invention of such a blade 2 is shown.
  • FIG. 2 are corresponding representations to FIG. 1 that is, in a) a section perpendicular to the axis of the rotor, in b) a view when inserting a blade and in c) a somewhat side view of an inserted blade.
  • an elevation 13 is arranged on the front end of the rotor 1 in the insertion direction 8 (on the abutment side 14), which may be referred to as a stop element 13.
  • this stop element 13 extends in the circumferential direction in each case between two adjacent recesses 4 over the entire tangential extent of the peripheral surface portions 5 and 5 '.
  • FIG. 2 shown possibility is manufacturing technology particularly easy to implement, since the rotor 1 can be easily formed in this case with a slightly larger peripheral radius for the peripheral surface 5, and milled in the direction of insertion 8 behind the stop element 13 areas around the entire circumference respectively turned off can (metallic subtracted feature).
  • stop elements 13 it is also possible to apply the stop elements 13 to some extent as ring sections on the peripheral surface portions 5, for example by screws, welding or soldering (metallic feature).
  • the stop member 13 has over FIG. 2b ) apparent in an axial section rectangular shape. But it is also possible to form the stop element 13 as a trapezoid or, to a certain extent, as a triangle, wherein the inclined flank of the blade 2 may be facing, and thereby a further wedge at deferred blade 2 results.
  • the blade 2 in turn has on the underside of the shroud 7 via a recess 12 corresponding to the stop element 13.
  • the recess 12 is arranged at the front end of the blade 2 in the direction of insertion 8.
  • the recess 12 has the corresponding female profile to a certain extent male stop element 13th
  • the stop element 13 defines the end position of the blade, since the blade is inserted until the recess 12 has completely absorbed the stop element 13 and impinges on its surface facing the axial direction.
  • the design according to the invention thus leads to the correct axial positioning of the blade.
  • the stepped shape can also be used in a very targeted manner to allow exactly a desired amount of air to flow through the gap, for example, for cooling.
  • the stopper member 13 is preferably formed with a width in the axial direction A in the range of 3-20 mm, and with a height in the radial direction R in the range from 1-20 mm.
  • FIG. 3 results in the proposed embodiment, the advantage that a scoop configured according to the invention also on an existing rotor 1, that is a rotor without stop element 13, can be pushed. Accordingly, the presence of the recess 12 does not disturb the compatibility of new blades with existing rotors. New blades can be easily installed on existing rotors (bucket retrofit). The resulting achievable and available flexibility allows a tremendous degree of freedom in retrofit applications.

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

Claims (10)

  1. Rotor pour une turbomachine, le rotor (1) étant conçu pour recevoir des aubes (2) qui forment au moins un étage d'aube dans la direction périphérique du rotor, le rotor disposant d'une pluralité d'évidements profilés (4) s'étendant essentiellement axialement par rapport à la surface du rotor, dont la forme correspond par engagement par correspondance géométrique et/ou par correspondance de forme aux profilés de base d'aubes (16) des aubes qui sont enfoncées essentiellement dans la direction axiale (8), et entre les évidements (4) dans la direction périphérique du rotor (1) étant prévues des portions de surface périphériques (5) qui sont pourvues d'éléments de butée (13) par rapport à une partie correspondante des aubes enfoncées, caractérisé en ce que les éléments de butée (13) sont disposés d'un côté de chaque portion de surface périphérique (5) par rapport à la direction d'enfoncement des aubes, en ce que chaque élément de butée (13) présente, par rapport à la portion de surface périphérique associée (5), une étendue radiale et axiale qui coïncide au moins par engagement par correspondance géométrique avec un évidement (12) de l'aube enfoncée, et en ce que la forme de l'élément de butée (13) et la forme de l'évidement (12) de l'aube forment un joint à labyrinthe entre le rotor et l'aube.
  2. Rotor selon la revendication 1, caractérisé en ce que les évidements (4) dans le rotor sont réalisés sous forme de profilés en queue d'aronde ou de profilés en sapin.
  3. Rotor selon la revendication 1, caractérisé en ce que le rotor (1) est configuré au niveau de la périphérie de telle sorte qu'un nombre identique ou différent d'aubes puisse être installé par étage.
  4. Rotor selon les revendications 1 à 3, caractérisé en ce que le rotor (1) et/ou les aubes est/sont réalisés avec des moyens qui permettent une fixation axiale dans la région avant ou arrière.
  5. Rotor selon la revendication 1, caractérisé en ce que l'évidement (12) de l'aube (2) est prévu dans le côté inférieur d'une bande de recouvrement (7) en tant que composant de la pale d'aube (9) disposée par-dessus, appartenant à l'aube.
  6. Rotor selon la revendication 1, caractérisé en ce que les éléments de butée (13) sont réalisés sous forme de portions annulaires sur les portions de surface périphériques (5, 5') avec une section transversale rectangulaire ou quadratique en coupe axiale.
  7. Rotor selon la revendication 1, caractérisé en ce que les éléments de butée (13) sont réalisés sur moins de 50 % de l'étendue axiale des portions de surface périphériques (5, 5').
  8. Rotor selon la revendication 1, caractérisé en ce que les éléments de butée (13) présentent une hauteur radiale dans une plage de 1-20 mm, et/ou une étendue axiale dans une plage de 3-20 mm.
  9. Rotor selon la revendication 1, caractérisé en ce que les éléments de butée (13) et les évidements (12) sont en affleurement les uns avec les autres et en ce que des moyens d'étanchéité sont disposés dans la région des bords.
  10. Rotor selon la revendication 1, caractérisé en ce que l'aube (2) présente en outre une bande de recouvrement supérieure.
EP08775236.6A 2007-08-08 2008-07-21 Agencement de rotor de turbine Not-in-force EP2183467B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH12582007 2007-08-08
PCT/EP2008/059507 WO2009019126A1 (fr) 2007-08-08 2008-07-21 Agencement de rotor de turbine

Publications (3)

Publication Number Publication Date
EP2183467A1 EP2183467A1 (fr) 2010-05-12
EP2183467B1 true EP2183467B1 (fr) 2015-11-18
EP2183467B2 EP2183467B2 (fr) 2023-10-18

Family

ID=39865717

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08775236.6A Not-in-force EP2183467B2 (fr) 2007-08-08 2008-07-21 Agencement de rotor de turbine

Country Status (6)

Country Link
US (1) US9435213B2 (fr)
EP (1) EP2183467B2 (fr)
JP (1) JP2010535968A (fr)
CA (1) CA2707510C (fr)
MX (1) MX2010001538A (fr)
WO (1) WO2009019126A1 (fr)

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US9109457B2 (en) * 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade
FR3026429B1 (fr) * 2014-09-30 2016-12-09 Snecma Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor
US20160230579A1 (en) * 2015-02-06 2016-08-11 United Technologies Corporation Rotor disk sealing and blade attachments system
KR101689085B1 (ko) 2015-08-03 2017-01-02 두산중공업 주식회사 터빈용 마지막 버켓 고정장치 및 이를 이용한 마지막 버켓의 조립 방법
DE102016222312B4 (de) * 2016-11-14 2025-12-31 Everllence Se Strömungsmaschinenrotor und Verfahren zum Herstellen desselben
FR3085420B1 (fr) 2018-09-04 2020-11-13 Safran Aircraft Engines Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine
FR3092865B1 (fr) * 2019-02-19 2021-01-29 Safran Aircraft Engines Disque de rotor avec arret axial des aubes, ensemble d’un disque et d’un anneau et turbomachine

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Publication number Priority date Publication date Assignee Title
US3047268A (en) 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
US3112914A (en) 1960-08-01 1963-12-03 Gen Motors Corp Turbine rotor
GB1527074A (en) 1974-09-28 1978-10-04 Rolls Royce Bladed rotors
DE3743253A1 (de) 1987-12-19 1989-06-29 Mtu Muenchen Gmbh Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen
EP0710766A1 (fr) 1994-11-05 1996-05-08 ROLLS-ROYCE plc Disque de rotor avec garniture d'étanchéité intégrée
WO1999050534A1 (fr) 1998-03-27 1999-10-07 Pratt & Whitney Canada Corp. Deflecteur servant a reguler l'entree de fuites d'air de refroidissement dans la trajectoire du gaz d'un moteur a turbine a gaz
EP1795706A1 (fr) 2005-12-07 2007-06-13 Honeywell International Inc. Disque de turbine de métallurgie des poudres plaqué platine pour une utilisation à température élevée

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"Zeichnungsblatt zur Laufscheibe", TURBINE, STUFE 1 DER MTR 390 (ZEICHNUNGSNUMMER: AH30014, 1988

Also Published As

Publication number Publication date
EP2183467A1 (fr) 2010-05-12
US20100166563A1 (en) 2010-07-01
WO2009019126A1 (fr) 2009-02-12
CA2707510A1 (fr) 2009-02-12
CA2707510C (fr) 2016-09-27
JP2010535968A (ja) 2010-11-25
EP2183467B2 (fr) 2023-10-18
US9435213B2 (en) 2016-09-06
MX2010001538A (es) 2010-03-15

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