WO2008122492A1 - Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement - Google Patents

Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement Download PDF

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Publication number
WO2008122492A1
WO2008122492A1 PCT/EP2008/053271 EP2008053271W WO2008122492A1 WO 2008122492 A1 WO2008122492 A1 WO 2008122492A1 EP 2008053271 W EP2008053271 W EP 2008053271W WO 2008122492 A1 WO2008122492 A1 WO 2008122492A1
Authority
WO
WIPO (PCT)
Prior art keywords
arrangement
securing
rotor
recess
blocking element
Prior art date
Application number
PCT/EP2008/053271
Other languages
German (de)
English (en)
Inventor
Darren T. Engle
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP08717999A priority Critical patent/EP2129871A1/fr
Priority to US12/594,353 priority patent/US20110027092A1/en
Priority to CN200880016327.0A priority patent/CN101680304B/zh
Priority to JP2010501467A priority patent/JP4942844B2/ja
Publication of WO2008122492A1 publication Critical patent/WO2008122492A1/fr

Links

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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the invention relates to an arrangement for axial securing of rotor blades in a rotor, with a shaft collar, on the outer circumference of which are provided in the axial direction of the rotor blade holding grooves, in each of which rotor blades with corresponding to the blade holding groove
  • Shovel feet are arranged, with one on a stirnseiti ⁇ gen side surface of the shaft collar, arranged in the region of the retaining projection in which a radially outwardly open circumferential groove is provided and arranged in each blade radially inwardly open securing grooves, each of the circumferential groove radially opposite, being provided for axial securing the Laufschaufein each engaging in the circumferential groove and in the securing groove sheet-shaped sealing elements which form a frontal sealing ring in the circumferential direction, wherein to secure the
  • Sealing elements against displacement in the circumferential direction of at least one of the sealing elements has a means. Furthermore, the invention relates to a gas turbine with such An ⁇ order.
  • FIG. 1 It also shows an arrangement according to FIG. 1. It shows a generic arrangement in a plan view and FIG. 2 in a cross section according to section line II-II in FIG. 1.
  • sealing elements are used two slightly overlapping sealing sheets 16 is provided, which cover in each case the frontal opening of the blade holding groove 12 in half.
  • Each sealing plate 16 is inserted at its radially inner end 18 in an end face on a rotor disk 19 provided circumferential groove 20 and at its radially outer end 22 in a
  • Securing groove 24 which is provided on the underside 26 of a platform 28 of the rotor blade 14.
  • a rectilinear sheet metal strip 30 is fixed to each, which extend substantially in the radial direction of the rotor 23.
  • Each sheet metal strip 30 terminates at its radially outer end 32 in a uniform converging point 34.
  • Chamfered edges 36 are provided on the platforms 28 of the rotor 14, with two opposite edges 36 of immediately adjacent turbine blades 14 forming a tapered recess 38 into which the tip 34 of the sheet metal strip 30 can protrude against the shift in the circumferential direction U to secure the sealing plate 16 and can rest.
  • the sealing plates 16 also provide for a separation of two areas 37, 39, in which on the one hand cooling air and on the other hand may enter a part of the hot gas.
  • two parallel slots 40 are provided in the latter, through which the already U-shaped pre-bent sheet metal strip 30 is ⁇ sets.
  • the tip 41 of the opposite end 41 of the sheet metal strip 30 is bent before the assembly of the sealing plate 16 on the rotor disk 19 in the position shown in FIG 2 for fixing the metal strip 30.
  • the sealing plates 16 are successively threaded with the pre-assembled metal strips 30 in the endless circumferential, arranged on the rotor disk 19 circumferential groove 20 and arranged in the bottom 26 of the platform 28 securing groove 24.
  • the sealing plates 16 are so along the circumference the circumferential groove 20 positions each sheet metal strip 30 opposite a recess 38. Subsequently, the tips 34 of the sheet metal stiffeners 30 are bent into the recesses 38 in order to preclude a displacement of the sealing sheets 16 in the circumferential direction U.
  • the sheet metal strips may only be bent once due to the extremely high mechanical requirements, in the case of service when replacing a blade, the strip of sheet metal that has then been raised must be replaced by a new sheet metal strip.
  • the slots provided for receiving the metal strips in the sealing sheets weaken the sealing sheets.
  • Object of the present invention is to provide an alternative arrangement for securing the sealing elements against a threatening in the circumferential direction shift, in which the assembly and disassembly times are improved. More ⁇ On transfer of the invention is to provide a gas turbine with such an arrangement.
  • the invention provides that in the generic arrangement, the means for securing the sealing elements against displacement in the circumferential direction provided in the sealing element opening and provided in the side surface of the shaft collar, with the opening approximately aligned recess and in the recess and in the opening includes seated position-secured blocking element.
  • the invention differs from the previous embodiment, in which a sheet metal strip entangled with the sealing element engages positively in a recess. Instead of the metal strip now a blocking element is provided in the front side on
  • Shaft collar provided recess can be used.
  • the blocking element blocks a displacement of the sealing element in the circumferential direction, since, in the region of the sealing element arranged, extending transversely to the circumferential groove, in which the sealing element sits and engages in the opening provided on the sealing element. A slight and tolerable play of the sealing element along the circumferential groove is only possible insofar as in
  • Width seen in the circumferential direction of the opening is greater than the width to be considered in the circumferential direction of the blocking element.
  • the blocking element which engages in the ⁇ ff ⁇ tion of the sealing element and the front side of the shaft ⁇ collar is fixed by a blocking element plastically deforming Anstemmung, a particularly reliable and easy axial securing of the sealing element against displacement in the circumferential direction can be achieved.
  • the assembly is quick and easy to accomplish.
  • the blocking element with a suitable Stemmwerkmaschine, such as tool on the type of hammer and chisel, plastically deform the front side, so that it rests in the recess under tension.
  • a very reliable frictional engagement between the wall of the recess and the blocking element is brought about, which reliably prevents the unwanted release of the blocking element during operation of the gas turbine.
  • the deformed region of the blocking element can be removed by grinding, thus loosening the frictional connection for removal.
  • sealing element omitted with the embodiment of the invention previously debilitating slots which were designed to buildin ⁇ account the locking plate on the sealing element.
  • the rigidity of the sealing element is thus further increased, as is its sealing effect.
  • the blocking element - based on its installation position - in the region of the recess in cross-section wedge-shaped and also includes a frontally outstanding bolt, which is insertable into the opening of the sealing element.
  • a defined position of the blocking element in the rotor is predetermined.
  • the orientation of the wedge shape of the recess is selected so that the mutually running side walls facing outward, as well as the corresponding edges of the blocking element.
  • the blocking element receiving recess is seen radially outwardly open.
  • the blocking element used in relation to the rotor can be plastically deformed circumferentially, instead of the frontal deformation. If then additionally circumferentially arranged pockets are provided in the side walls of the recess, can escape into the parts of the deformed material of the blocking element, in addition to the jamming of the blocking element also a positive connection for securing the position of the blocking element can be provided.
  • the blocking element is secured against loss particularly reliable.
  • the opening provided on the sealing element is then provided at the radially inner end of the sealing element. This area of the log message ⁇ ments heated at least during operation, so that the stiffness and temperature resistance of the seal member through the opening are not affected.
  • every second or each sealing element has the means for securing the sealing elements against displacement.
  • the arrangement is provided on a rotor of a sta tionary ⁇ , passing through in the axial direction of the gas turbine.
  • FIG. 1 shows the arrangement for the axial securing of a sliding disk in a rotor according to the prior art
  • FIG. 2 shows the cross-sectional view according to FIG. 1 along the section line II-II, FIG.
  • FIG. 3 shows the detail of a plan view of a rotor disk with a ⁇ arranged thereon as a blade assembly for an axial securing of the blade by means of a sealing element
  • FIG. 4 shows a perspective view of a blocking element according to the invention
  • FIG. 3 shows a section of the frontal plan view of the shaft collar 21 formed by a rotor disk 19 a rotor 23 of a gas turbine.
  • the rotatable around the axis of rotation 50 rotor 23 has distributed on its outer circumference along the circumference 52 U, extending in the axial direction running ⁇ scoop holding grooves 12, in each of which a blade 14 with the bucket holding groove 12 corresponds executed ⁇ tem blade foot 54 can be inserted.
  • a blade 14 has already been inserted.
  • a projection 58 extending in the axial direction or widening with a circumferential groove 20 open radially outwards is arranged on an end face of the rotor disk 19 or on an end face 56 of the shaft collar 21.
  • the circumferential groove 20 is arranged, for example, radially further inward than the blade retaining grooves 12.
  • the rotor blade 14 has a platform arranged between the blade root 54 and profiled blade 28, on the underside of which an open groove 20 is provided for the locking groove 24, while being opposite this.
  • a sealing element 42 is inserted into the endless circumferential groove 20 and into the securing groove 24 which secures the blade 14 against displacement along the blade holding groove.
  • the sealing element 42 covers the frontal opening of one of the running ⁇ blade retaining grooves 12 completely.
  • the sealing elements 42 are secured by one of the sealing elements 42 against displacement along the blade retaining groove 12.
  • sealing elements 42 may also be distributed over the circumference, as in the prior art, so that two immediately adjacent sealing elements each engage in half in the securing groove 24 of the blade 14. Then, two adjacent seal members secure one of the blades 14 against axial displacement.
  • Analogous to the prior art forms a completely montier ⁇ ter ring of sealing elements 42, which overlap each slightly, a sealing ring, the ab separates a through which a coolant region 37 from another region 39 in which a hot gas can occur under certain circumstances (FIG 2).
  • an opening 63 is provided at the radially inner end 61 of the sealing element 42, which can be a notch, but also a bore.
  • a recess 65 is provided on the side surface 56 of the shaft collar 21 in the region of the projection 58, which recess is substantially in the axial direction of the
  • Rotor 23, d. H. runs parallel to the axis of rotation 50.
  • Each recess 65 has two opposite side surfaces 66, which, viewed from the outside, extend in a wedge shape toward one another, but do not touch each other to form a gap.
  • an outwardly closed recess may be present.
  • the two mutually extending side walls 66 touch in a rounded tip.
  • the blocking element 67 shown in perspective in FIG. 4 can be used.
  • the blocking element 67 comprises a section with a wedge shape corresponding to the recess 65 with flanks 70 extending toward one another and a bolt 69 arranged on the wedge-shaped section.
  • a slight and tolerable game of the sealing element 42 along the circumferential groove 20 is possible only insofar as seen in circumferential direction width of the opening 63 is big ⁇ SSER than that to be viewed in the circumferential direction width or the diameter of the bolt.
  • the width of the opening 63 in the Wesentli ⁇ chen speaks to the diameter of the bolt 69th
  • the former After insertion of the blocking element 67 in the recess 65, the former is slightly plastically deformed by means of a Anstemmvorgangs.
  • the blocking element 67 is plastically deformed in the area 71.
  • the flanks 70 are pressed against the side walls 66. This results in a reliable frictional engagement between the walls 66 of the recess 65 and those flanks 70 of the blocking element 67, which reliably prevents the unwanted release of the latter.
  • the Anstemmvorgang can be done by means of a suitable, slightly rounded at the top bit, which is attached to the blocking element in the area 71, provided with a hammer blow.
  • the blocking element has a front-side pre-machined recess 71, in which the chisel is to be set.
  • FIG. 4 An alternative embodiment of the invention is shown in perspective in FIG.
  • the blocking element 67 shown in FIG 4 is used with only a slight change in the recess 65.
  • the front-side trough 71 has to be used for FIG 5
  • Blocking element 67 two - relative to the rotor - shell-side (circumferential) troughs 71 as an aid to the Anstemmvorgang on if the blocking element 67 is inserted in the recess 65 shown in FIG 5, each opposite one in the side walls 66 circumferentially provided pockets 72.
  • the troughs 71 adjacent material of the blocking element can be introduced into the pockets 72, so that there is a positive connection for secure positioning of the blocking element 67 in the recess 65.
  • the invention provides an arrangement in which the known from the prior art disadvantages are eliminated by a blocking element inserted from the end face of the shaft collar into a recess blocking the displacement of the sealing element. So that the blocking element itself is secured against unintentional loosening, this is fastened to the rotor disk by means of a plastic deformation.

Landscapes

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

Abstract

L'invention concerne un agencement (10) pour ailettes de rotor (14), comprenant un collet d'arbre (21) sur la périphérie externe (52) duquel sont prévues des gorges porte-ailettes (12) dans lesquelles sont respectivement des ailettes (14), avec une saillie placée sur une face latérale (56) du collet d'arbre (21), côté face frontale, dans la zone des gorges de support, ladite saillie présentant une gorge périphérique (20) ouverte vers l'extérieur et des gorges de fixation (24) ouvertes vers l'intérieur sont disposées radialement dans chaque ailette (14), lesdites gorges de fixation étant respectivement radialement en regard de la gorge périphérique (20). Pour la fixation axiale des ailettes (14), des éléments d'étanchéité (42) de type tôle sont respectivement insérées dans la gorge périphérique (20) et dans la gorge de fixation (24). À titre de variante de la fixation des éléments d'étanchéité (42) visant à empêcher tout déplacement dans la gorge (20) dans la direction périphérique, l'invention propose qu'un élément de blocage (67) inséré depuis la face frontale du collet d'arbre (21) dans un évidement (65) bloque le trajet de déplacement de l'élément d'étanchéité (42). Pour empêcher que l'élément de blocage (67) lui-même ne se détache involontairement, il est fixé au disque de rotor par déformation plastique.
PCT/EP2008/053271 2007-04-04 2008-03-19 Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement WO2008122492A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP08717999A EP2129871A1 (fr) 2007-04-04 2008-03-19 Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement
US12/594,353 US20110027092A1 (en) 2007-04-04 2008-03-19 Arrangement for axially securing rotating blades in arotor, and gas turbine having such an arrangement
CN200880016327.0A CN101680304B (zh) 2007-04-04 2008-03-19 工作叶片在转子上的轴向保险装置和有这种装置的燃气轮机
JP2010501467A JP4942844B2 (ja) 2007-04-04 2008-03-19 ロータにおける動翼の軸方向固定構造とその軸方向固定構造を備えたガスタービン

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07007088.3 2007-04-04
EP07007088A EP1978211A1 (fr) 2007-04-04 2007-04-04 Dispositif de sécurité axiale sur des aubes mobiles d'un moteur tout comme turbine à gaz dotée d'un tel dispositif

Publications (1)

Publication Number Publication Date
WO2008122492A1 true WO2008122492A1 (fr) 2008-10-16

Family

ID=38372409

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/053271 WO2008122492A1 (fr) 2007-04-04 2008-03-19 Agencement pour fixation axiale à des ailettes de rotor et turbine à gaz dotée d'un tel agencement

Country Status (6)

Country Link
US (1) US20110027092A1 (fr)
EP (2) EP1978211A1 (fr)
JP (1) JP4942844B2 (fr)
CN (1) CN101680304B (fr)
RU (1) RU2427713C2 (fr)
WO (1) WO2008122492A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101936191A (zh) * 2009-06-30 2011-01-05 通用电气公司 用于组装旋转机器的方法及设备

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218873A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Section de rotor pour un rotor d'une turbomachine, aube directrice pour une turbomachine et élément de blocage
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
US9745852B2 (en) 2012-05-08 2017-08-29 Siemens Aktiengesellschaft Axial rotor portion and turbine rotor blade for a gas turbine
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz
EP2940249A1 (fr) * 2014-04-29 2015-11-04 Siemens Aktiengesellschaft Agencement de disque de roue et procédé de montage d'un agencement de disque de roue
FR3021691B1 (fr) * 2014-06-03 2016-06-24 Snecma Rotor pour turbomachine comportant des aubes a plates-formes raportees
EP3048256A1 (fr) 2015-01-20 2016-07-27 Siemens Aktiengesellschaft Rotor comportant une aube de turbine avec un dispositif de verrouillage
CN105065065A (zh) * 2015-08-07 2015-11-18 山东青能动力股份有限公司 一种枞树型叶根动叶片锁紧装置及其装配工艺
EP3611344A1 (fr) * 2018-08-16 2020-02-19 Siemens Aktiengesellschaft Rotor à protection de circonférence des éléments d'étanchéité
US11021974B2 (en) * 2018-10-10 2021-06-01 Rolls-Royce North American Technologies Inc. Turbine wheel assembly with retainer rings for ceramic matrix composite material blades

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GB739870A (en) * 1954-04-07 1955-11-02 Parsons C A & Co Ltd Improvements in and relating to locking devices for rotor blades of turbines and the like
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US3957393A (en) * 1974-10-29 1976-05-18 United Technologies Corporation Turbine disk and sideplate construction
DE19516694A1 (de) * 1995-05-06 1996-11-07 Mtu Muenchen Gmbh Einrichtung zur Fixierung von Laufschaufeln am Laufrad, insbesondere einer Turbine eines Gasturbinentriebwerks

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US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
FR2524933B1 (fr) * 1982-04-13 1987-02-20 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur
US4725200A (en) * 1987-02-24 1988-02-16 Westinghouse Electric Corp. Apparatus and method for reducing relative motion between blade and rotor in steam turbine
JPH02140403A (ja) * 1988-11-18 1990-05-30 Toshiba Corp タービン動翼の取付支持構造
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JPH0658102A (ja) * 1992-08-05 1994-03-01 Hitachi Ltd ガスタービン動翼
JPH09177502A (ja) * 1995-12-22 1997-07-08 Toshiba Corp タービン翼の固定方法
JP4498964B2 (ja) * 2005-03-30 2010-07-07 株式会社日立製作所 タービン動翼及びこれを用いたタービン設備

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB739870A (en) * 1954-04-07 1955-11-02 Parsons C A & Co Ltd Improvements in and relating to locking devices for rotor blades of turbines and the like
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US3957393A (en) * 1974-10-29 1976-05-18 United Technologies Corporation Turbine disk and sideplate construction
DE19516694A1 (de) * 1995-05-06 1996-11-07 Mtu Muenchen Gmbh Einrichtung zur Fixierung von Laufschaufeln am Laufrad, insbesondere einer Turbine eines Gasturbinentriebwerks

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101936191A (zh) * 2009-06-30 2011-01-05 通用电气公司 用于组装旋转机器的方法及设备

Also Published As

Publication number Publication date
EP1978211A1 (fr) 2008-10-08
CN101680304B (zh) 2013-09-04
JP2010523873A (ja) 2010-07-15
CN101680304A (zh) 2010-03-24
EP2129871A1 (fr) 2009-12-09
RU2427713C2 (ru) 2011-08-27
JP4942844B2 (ja) 2012-05-30
US20110027092A1 (en) 2011-02-03
RU2009140744A (ru) 2011-05-10

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