EP1978211A1 - Dispositif de sécurité axiale sur des aubes mobiles d'un moteur tout comme turbine à gaz dotée d'un tel dispositif - Google Patents

Dispositif de sécurité axiale sur des aubes mobiles d'un moteur tout comme turbine à gaz dotée d'un tel dispositif Download PDF

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Publication number
EP1978211A1
EP1978211A1 EP07007088A EP07007088A EP1978211A1 EP 1978211 A1 EP1978211 A1 EP 1978211A1 EP 07007088 A EP07007088 A EP 07007088A EP 07007088 A EP07007088 A EP 07007088A EP 1978211 A1 EP1978211 A1 EP 1978211A1
Authority
EP
European Patent Office
Prior art keywords
rotor
recess
securing
blocking element
arrangement
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Withdrawn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
EP07007088A
Other languages
German (de)
English (en)
Inventor
Darren T. Engle
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 EP07007088A priority Critical patent/EP1978211A1/fr
Priority to RU2009140744/06A priority patent/RU2427713C2/ru
Priority to CN200880016327.0A priority patent/CN101680304B/zh
Priority to JP2010501467A priority patent/JP4942844B2/ja
Priority to PCT/EP2008/053271 priority patent/WO2008122492A1/fr
Priority to US12/594,353 priority patent/US20110027092A1/en
Priority to EP08717999A priority patent/EP2129871A1/fr
Publication of EP1978211A1 publication Critical patent/EP1978211A1/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Withdrawn legal-status Critical Current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
    • F01D5/3007—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, having 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 blades are arranged with the bucket feet corresponding blade feet, with a front 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, which in each case the circumferential groove radially opposite, wherein for axial securing of the blades in the circumferential groove and in the securing groove engaging sheet metal-shaped sealing elements are provided which form a frontal sealing ring in the circumferential direction, wherein for securing the sealing elements against displacement in the circumferential direction of at least one of the sealing elements a means having. Furthermore, the invention relates to a gas turbine with such an arrangement.
  • FIG. 1 shows such an arrangement in a plan view and FIG. 2 in a cross section along the section line II-II in FIG. 1 ,
  • two slightly overlapping sealing plates 16 are provided as sealing elements, each covering half of the end opening of the blade holding groove 12.
  • Each sealing plate 16 is inserted at its radially inner end 18 in an end face provided on a rotor disk 19 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 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 uniformly converging tip 34.
  • Chamfered edges 36 are provided on the platforms 28 of the blades 14, 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 used.
  • the tip 34 opposite the end 41 of the metal strip 30 is already in front of the assembly of the sealing plate 16 on the rotor disk 19 in the in FIG. 2 shown position for fixing the sheet metal strip 30 bent.
  • 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 positioned along the circumference of the circumferential groove 20 such that each sheet metal strip 30 faces 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 plates 16 in the circumferential direction U.
  • the metal strips may be bent only once due to the enormously high mechanical requirements, in the service case when replacing a blade of the then unfurled sheet metal strip is 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 threat of circumferential displacement, in which the assembly and disassembly times are improved.
  • Another object 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, which can be used in the front side provided on the shaft collar recess.
  • the blocking element blocks a displacement of the sealing element in the circumferential direction, since it, arranged in the region of the sealing element, extends 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 By using a blocking element, which engages in the opening of the sealing element and the front side is secured to the shaft collar by plastic deformation, 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.
  • the sealing element previously debilitating slots, which were provided for attachment of 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. Due to the wedge shape of the blocking element and the recess corresponding to the wedge shape is a defined position of the Locking element specified in the rotor. In addition, 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 wedge-shaped blocking element will strive outward under the action of centrifugal force and thereby become wedged or jammed in the recess, which further increases the frictional engagement between the flanks and the side walls and further complicates unintentional release of the blocking element. Consequently, a particularly secure arrangement can be specified.
  • 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. As a result, 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 sealing element heats up the least during operation, so that the rigidity and the temperature resistance of the sealing element are not impaired by the opening.
  • 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 stationary gas turbine flowing in the axial direction.
  • FIG. 3 shows a section of the frontal plan view of the formed by a rotor disk 19 shaft collar 21 of a rotor 23 of a gas turbine.
  • the rotatable around the axis of rotation 50 rotor 23 has at its outer periphery 52 along the circumference U distributed, extending in the axial direction blade holding grooves 12, in each of which a blade 14 with the blade holding groove 12 corresponds executed blade root 54 can be inserted.
  • Centrally shown blade holding groove 12 is already a Blade 14 inserted.
  • 2 darg Why the prior art is arranged on an end face of the rotor disk 19 and on a front side surface 56 of the shaft collar 21 extending in the axial direction projection 58 or widening with a radially outwardly open circumferential groove 20.
  • the circumferential groove 20 is arranged, for example, radially further inward than the blade retaining grooves 12.
  • the rotor blade 14 has a platform 28 arranged between the blade root 54 and the profiled blade, on the underside of which a securing groove 24 open to the circumferential groove 20 is provided and in the process lies opposite to it.
  • 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 retaining groove.
  • the sealing element 42 completely covers the end opening of one of the blade retaining grooves 12.
  • 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 sealing elements secure one of the blades 14 against axial displacement.
  • a completely assembled ring of sealing elements 42 each of which overlaps slightly, forms a sealing ring which separates a region 37 through which a coolant can flow from a further region 39 in which a hot gas may possibly occur ( FIG. 2 ).
  • an opening 63 is provided at the radially inner end 61 of the sealing element 42, which may 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 essentially 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.
  • FIG. 4 perspective blocking element 67 shown 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.
  • the means for securing the sealing element 42 against displacement in the circumferential direction U comprises the opening 63 in the sealing element 42, the recess 65 arranged in the end face of the rotor disk 19 and the blocking element 67 which can be inserted therein.
  • the width of the opening 63 preferably corresponds substantially to the diameter of the bolt 69.
  • 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. 5 An alternative embodiment of the invention is in FIG. 5 shown in perspective. It is from the FIG. 4 shown blocking element 67 with only a slight change in the recess 65 used.
  • the front-side trough 71 has for FIG. 5 to be used blocking element 67 two - relative to the rotor - shell-side (peripheral) troughs 71 as an aid to the Anstemmvorgang, which provided the blocking element 67 in the recess 65 according to FIG. 5 is used, each one in the side walls 66 peripherally provided pockets 72 opposite each other.
  • the troughs 71 adjacent Material of the blocking element are 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07007088A 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 Withdrawn EP1978211A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
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
RU2009140744/06A RU2427713C2 (ru) 2007-04-04 2008-03-19 Устройство для осевой фиксации рабочих лопаток в роторе и газовая турбина с таким устройством
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
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
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
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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
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
EP1978211A1 true EP1978211A1 (fr) 2008-10-08

Family

ID=38372409

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07007088A Withdrawn 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
EP08717999A Withdrawn 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

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08717999A Withdrawn 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

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 (3)

* 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
WO2013167346A1 (fr) * 2012-05-08 2013-11-14 Siemens Aktiengesellschaft Aube mobile de turbine et section axiale de rotor pour une turbine à gaz
EP3611344A1 (fr) * 2018-08-16 2020-02-19 Siemens Aktiengesellschaft Rotor à protection de circonférence des éléments d'étanchéité

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8251668B2 (en) * 2009-06-30 2012-08-28 General Electric Company Method and apparatus for assembling rotating machines
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
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
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
KR102887773B1 (ko) * 2023-04-04 2025-11-17 두산에너빌리티 주식회사 터빈 블레이드의 씰 조립구조와 이를 포함하는 가스 터빈

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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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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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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 (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
WO2010094539A1 (fr) * 2009-02-17 2010-08-26 Siemens Aktiengesellschaft Segment de rotor pour le rotor d'une turbomachine, aube mobile pour une turbomachine
KR20110136894A (ko) * 2009-02-17 2011-12-21 지멘스 악티엔게젤샤프트 터보 기계의 로터용 로터 섹션
CN102317577A (zh) * 2009-02-17 2012-01-11 西门子公司 用于涡轮机的转子的转子部分、用于涡轮机的转子叶片
EP2426315A1 (fr) * 2009-02-17 2012-03-07 Siemens Aktiengesellschaft Section de rotor pour un rotor d'une turbomachine
US8888460B2 (en) 2009-02-17 2014-11-18 Siemens Aktiengesellschaft Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine
US8894371B2 (en) 2009-02-17 2014-11-25 Siemens Aktiengesellschaft Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine
WO2013167346A1 (fr) * 2012-05-08 2013-11-14 Siemens Aktiengesellschaft Aube mobile de turbine et section axiale de rotor pour une turbine à gaz
US9745852B2 (en) 2012-05-08 2017-08-29 Siemens Aktiengesellschaft Axial rotor portion and turbine rotor blade for a gas turbine
EP3611344A1 (fr) * 2018-08-16 2020-02-19 Siemens Aktiengesellschaft Rotor à protection de circonférence des éléments d'étanchéité

Also Published As

Publication number Publication date
RU2009140744A (ru) 2011-05-10
CN101680304B (zh) 2013-09-04
WO2008122492A1 (fr) 2008-10-16
JP2010523873A (ja) 2010-07-15
RU2427713C2 (ru) 2011-08-27
CN101680304A (zh) 2010-03-24
EP2129871A1 (fr) 2009-12-09
US20110027092A1 (en) 2011-02-03
JP4942844B2 (ja) 2012-05-30

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