EP2107219A1 - Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement - Google Patents

Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement Download PDF

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Publication number
EP2107219A1
EP2107219A1 EP08006814A EP08006814A EP2107219A1 EP 2107219 A1 EP2107219 A1 EP 2107219A1 EP 08006814 A EP08006814 A EP 08006814A EP 08006814 A EP08006814 A EP 08006814A EP 2107219 A1 EP2107219 A1 EP 2107219A1
Authority
EP
European Patent Office
Prior art keywords
segment
guide
toothing
carrier
outer ring
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Withdrawn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
EP08006814A
Other languages
German (de)
English (en)
Inventor
Alexandra Küpper
Walter Loch
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
Original Assignee
Siemens 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
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08006814A priority Critical patent/EP2107219A1/fr
Priority to EP09728766A priority patent/EP2257695A1/fr
Priority to US12/935,995 priority patent/US8708648B2/en
Priority to CN200980111994.1A priority patent/CN101983280B/zh
Priority to PCT/EP2009/051529 priority patent/WO2009121653A1/fr
Priority to JP2011502309A priority patent/JP5100886B2/ja
Publication of EP2107219A1 publication Critical patent/EP2107219A1/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Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2220/31—Application in turbines in steam 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
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods

Definitions

  • the invention relates to a diaphragm segment and a guide vane carrier for a horizontally split turbomachine housing and a method for input and / or Auskugeln the disc segment in and out of the vane carrier.
  • a turbomachine is, for example, a gas turbine with a compressor in Axialbauweise.
  • the compressor has a horizontally split housing, whereby internal components of the compressor can be mounted in the detached from each other housing halves.
  • Fig. 4 and 5 For example, the assembly of a diaphragm segment 102 into a compressor housing 101 is shown.
  • the disk segment 102 forms a 180 ° half of the entire guide disk so that two finely arranged segments 102 of the disk form a guide disk.
  • the diaphragm segment 102 is mounted in the lower part of the compressor housing 101, wherein the assembly is accomplished by means of a mounting device 103, as shown in FIG Fig. 4 is shown.
  • the mounting device 103 is modeled on the diaphragm segment 102 and has plates 104 to which the diaphragm segment 102 is attached.
  • Phase 0 is shown, the disc segment 102 is embedded in the lower part of the compressor housing 101, whereas the mounting device 103 protrudes upwards.
  • the mounting device 103 is completely encompassed by the lower part of the compressor housing 101 and the diaphragm segment 102 protrudes upward from the compressor housing 101. After releasing the plates 104 from the diaphragm segment 102, the diaphragm segment 102 may be removed from the compressor housing 101.
  • the in- and Auskugeln the Leitusionnsegments 102 under operation of the crane is cumbersome, time-consuming and requires a high level of skill.
  • the object of the invention is to provide a disc segment and a guide vane carrier for a horizontally split turbomachinery housing and a method for input and / or Auskugeln the disc segment in or out of the vane carrier, wherein the disc segment quickly and reliably into and out of the Guide vane one-and / or auskugelbar is.
  • the horizontal split turbomachinery housing poppet segment of the present invention includes a plurality of vanes and an outer ring segment on which the vanes are disposed along its inner circumference and which is engageable within and / or out of a vane support of the turbomachine housing, the outer ring segment along its outer circumference has a toothing, in which a drive device engageable and with a tangential force on the outer ring segment can be applied, so that when introducing and / or Auskugeln the disc segment is drivable.
  • the guide vane carrier according to the invention for the horizontally divided turbomachinery housing, in and / or auskugelbar a disc segment has a helical element with a helical toothing, which is engageable in a provided along the outer periphery of the disc segment toothing, so that when turning of the screw element about its longitudinal axis a tangential force can be applied to the disc segment with which the disc segment is driven during the input and / or Auskugeln.
  • the method according to the invention for introducing and / or ejecting the disk segment into and / or out of the guide blade carrier comprises the steps of: providing the disk segment and the stator carrier; Rotating the worm member so that the vane segment is circumferentially driven by the worm member, wherein the vane segment is nested within the vane support or dislodged from the vane support.
  • the guide disk segment has at its outer ring segment the toothing in which the worm element engages with its helical toothing.
  • the helical gearing of the worm member is helically formed about the longitudinal axis of the worm member such that as the worm member is rotated about its longitudinal axis, the washer segment is circumferentially driven on the outer race segment.
  • the force acting on the disc segment force which is necessary for its movement, according to the invention always acts tangentially on the disc segment.
  • forces acting obliquely on the compressor housing or the visor segment are avoided. which could possibly lead to damage or wear.
  • the toothing of the outer ring segment is a globoid toothing and preferably the helical toothing of the screw element is a globoid toothing.
  • the contact region of the toothing of the outer ring and the helical toothing of the screw element is formed flat, whereby the wear is low, in particular at the helical toothing of the screw element.
  • the globoid teeth have a concave structure in each of the planes in which the longitudinal axis of the turbomachine housing is located.
  • the worm element is at least partially encompassed by the globoid toothing of the outer ring segment, as a result of which the contact surface of the outer ring segment with the worm element is large.
  • the worm member is rotatably guided with its helical toothing, which engages in the toothing of the outer ring segment, whereby a tilting of the screw element in the toothing of the outer ring segment is prevented.
  • the concave contour of the globoid toothing of the outer ring segment describes a quarter circle.
  • the globoid toothing of the outer ring segment can advantageously be provided, for example, in the region of an imaginary outer edge of the outer ring segment, as a result of which the control disc segment is easy to produce and the screw element is easily accessible from the outside.
  • the vane support has a blind hole with a bottom on which the screw element is supported.
  • the worm element has an inner polyhedron profile on which the worm element can be driven by means of a tool which can be cooperated with the inner polyhedron profile.
  • the tool can be designed, for example, as a crank with an external hexagonal profile, which can be inserted into the internal polygonal profile of the screw element. If the crank is turned by hand, the screw element is rotated and the disc segment easily and conveniently dislocated from the vane support or nested in the vane support.
  • the worm element is mounted only for input and / or Auskugeln the disc segment on the vane support.
  • the screw member may be removed from the vane carrier.
  • the auger element may also be mounted in the vane support during operation of the turbomachine.
  • Fig. 1 to 3 has an axial compressor 1, a compressor housing 2, which is divided horizontally.
  • a guide blade carrier 3 is provided, which has on its inner circumference a circumferential groove 4 for receiving a guide disk segment 5.
  • Fig. 1 the compressor rotor with the compressor blades arranged thereon not shown.
  • the disc segment 5 extends over a circumferential angle of 180 °.
  • Each disc segment 5 has a plurality of circumferentially juxtaposed vanes 6, so that two juxtaposed discs segment 5 form a complete guide disc for the compressor 1.
  • the guide vanes 6 of the guide plate then form in their entirety a guide vane grille of the compressor.
  • the diaphragm segment 5 has on its outer edge an outer ring segment 7 and on its inner circumference an inner ring segment 8, wherein between the outer ring segment 7 and the inner ring segment 8, the guide vanes 6 are arranged radially.
  • the vanes 6 are formed elongated, wherein an outer longitudinal end of the outer ring segment 7 and an inner longitudinal end of the inner ring segment 8 is pivotally mounted.
  • the guide vanes 6 are pivotable about their longitudinal axis by means of an adjusting mechanism 9, the adjusting mechanism 9 being accessible from outside the compressor housing 2.
  • the guide vanes 6 of the baffle form the pivotable inlet guide vanes of the compressor.
  • the guide disc segment 5 engages with its outer ring segment 7 in the circumferential groove 4, wherein the guide blade carrier 3 may be part of the compressor housing 2. To disassemble the disc segment 5 by 180 °, ie from the guide vane carrier 3 to rotate until the outer ring segment 7 is out of engagement with the circumferential groove 4.
  • the outer ring segment 7 has at an imaginary outer peripheral edge of a globoid toothing 10 which is formed in each plane in which the longitudinal axis of the guide blade carrier 3 is quarter-circle-shaped.
  • the vane support 3 has a screw member 11 having a cylindrical shape.
  • a helical toothing 12 is provided, which is designed such that it can cooperate with the globoid toothing 10 to form a worm drive.
  • the screw element 11 is arranged in a blind hole 14, which is provided in the guide blade carrier 3, so that the screw element 11 is held in the blind hole 14, while the screw element engages with its helical toothing 12 over a quarter circle circumference in the globoid toothing 10.
  • the blind hole 14 has a bottom 15, on which the screw element 11 is supported in the longitudinal direction thereof. Further, the screw member 11 at its front side, the bottom 15 facing away from a hexagon socket 13 on.
  • a crank engageable with a suitably formed mecanicsechskantprofil.
  • the worm element 11 forms with the outer ring segment 7 via the helical gearing 12 and the globoid gearing 10, the worm drive. Due to frictional forces that occur in particular when moving the outer ring segment 7 in the circumferential groove 4, the screw element 11 is pressed into the blind hole 14. In this case, the screw element 11 is stably supported on the bottom 15.
  • the screw element 11 can be removed from the blind hole 14 so that upon further treatment of the axial compressor or its operation, the screw element 11 is not housed in the blind hole 14 of the vane support 3. Conversely, when the screw member 11 for mounting or dismounting the diaphragm segment fifth should not be provided separately, the screw element 11 remain in the blind hole 14 during operation of the axial compressor 1.
  • the disc segment according to the invention and the associated drive can be applied not only to inlet guide vanes of a compressor, but also downstream of arranged Leitschaufelringen, whose vanes are possibly also pivotable about their longitudinal axes.
  • the input and / or Auskugeln the baffle 5 can also be done with inserted in the lower half of the rotor housing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08006814A 2008-04-03 2008-04-03 Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement Withdrawn EP2107219A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP08006814A EP2107219A1 (fr) 2008-04-03 2008-04-03 Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement
EP09728766A EP2257695A1 (fr) 2008-04-03 2009-02-11 Appareil pour un carter de turbomachine divisé horizontalement, segment de disques de guidage et support d aube directrice pour un carter de turbomachine divisé horizontalement
US12/935,995 US8708648B2 (en) 2008-04-03 2009-02-11 Device for a horizontally split turbomachine housing, guide vane ring segment and guide vane carrier for a horizontally split turbomachine housing
CN200980111994.1A CN101983280B (zh) 2008-04-03 2009-02-11 用于水平分开的透平机外壳的装置、导向轮部段和用于水平分开的透平机外壳的导向叶片外圈
PCT/EP2009/051529 WO2009121653A1 (fr) 2008-04-03 2009-02-11 Appareil pour un carter de turbomachine divisé horizontalement, segment de disques de guidage et support d’aube directrice pour un carter de turbomachine divisé horizontalement
JP2011502309A JP5100886B2 (ja) 2008-04-03 2009-02-11 水平分割式タービン車室用静翼輪据付装置及び静翼ホルダ並びに静翼輪セグメントの組立分解方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08006814A EP2107219A1 (fr) 2008-04-03 2008-04-03 Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement

Publications (1)

Publication Number Publication Date
EP2107219A1 true EP2107219A1 (fr) 2009-10-07

Family

ID=39735346

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08006814A Withdrawn EP2107219A1 (fr) 2008-04-03 2008-04-03 Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement
EP09728766A Withdrawn EP2257695A1 (fr) 2008-04-03 2009-02-11 Appareil pour un carter de turbomachine divisé horizontalement, segment de disques de guidage et support d aube directrice pour un carter de turbomachine divisé horizontalement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09728766A Withdrawn EP2257695A1 (fr) 2008-04-03 2009-02-11 Appareil pour un carter de turbomachine divisé horizontalement, segment de disques de guidage et support d aube directrice pour un carter de turbomachine divisé horizontalement

Country Status (5)

Country Link
US (1) US8708648B2 (fr)
EP (2) EP2107219A1 (fr)
JP (1) JP5100886B2 (fr)
CN (1) CN101983280B (fr)
WO (1) WO2009121653A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2728130A1 (fr) * 2012-10-30 2014-05-07 Siemens Aktiengesellschaft Dispositif auxiliaire
EP3009604A1 (fr) * 2014-09-19 2016-04-20 United Technologies Corporation Système d'aubes fixes-variables fixées radialement

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012202468B3 (de) 2012-02-17 2013-07-04 Siemens Aktiengesellschaft Turbomaschine
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
EP2706198A1 (fr) * 2012-09-10 2014-03-12 Alstom Technology Ltd Procédé pour supprimer un coffrage interne d'une machine
US8844107B2 (en) * 2012-11-09 2014-09-30 General Electric Company System for assembling and disassembling a turbine section of a gas turbine
JP6082285B2 (ja) * 2013-03-14 2017-02-15 三菱日立パワーシステムズ株式会社 静翼環の取外・取付方法、及びこの方法に用いる静翼セグメントの補助支持装置
CN104097037B (zh) * 2014-06-26 2016-04-20 哈尔滨电气动力装备有限公司 核电站核主泵导叶的加工工艺
JP6547534B2 (ja) * 2015-09-14 2019-07-24 株式会社Ihi 軸流機械の分解方法
JP7011952B2 (ja) 2018-03-01 2022-01-27 三菱パワー株式会社 静翼セグメント、及びこれを備えている蒸気タービン
CN112065777B (zh) * 2020-11-10 2021-01-19 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构

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US2488867A (en) * 1946-10-02 1949-11-22 Rolls Royce Nozzle-guide-vane assembly for gas turbine engines
US2918253A (en) * 1956-05-18 1959-12-22 Orenda Engines Ltd Rotor assemblies for turbines
JPS6081402A (ja) * 1983-10-13 1985-05-09 Toshiba Corp 蒸気タ−ビンのノズルダイアフラム支持装置
DE102005021446B3 (de) * 2005-05-04 2006-06-29 Technische Universität Dresden Gasturbine
WO2006103152A1 (fr) * 2005-03-29 2006-10-05 Alstom Technology Ltd Procede et dispositif pour remplacer des pieces d'une machine hydraulique rotative
WO2008012195A1 (fr) * 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire

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US5018942A (en) * 1989-09-08 1991-05-28 General Electric Company Mechanical blade tip clearance control apparatus for a gas turbine engine
US5605071A (en) * 1995-06-06 1997-02-25 Itt Automotive Electrical Systems, Inc. Enveloped worm gear clutch wedgelock responsive to reaction force
JP2925501B2 (ja) * 1996-08-30 1999-07-28 株式会社サカエ金型工業 ウォームホイール射出成形用金型の製造方法
US5992259A (en) * 1996-10-16 1999-11-30 Fleytman; Yakov Worm/wormgear transmission and apparatus for transmitting rotation utilizing an oscillating input
US6155136A (en) * 1999-01-15 2000-12-05 Milton Roy Company Gear shaft assembly and method of making the same
JP3201749B2 (ja) * 1999-05-27 2001-08-27 西日本プラント工業株式会社 タービンロータ等の大型回転体の保守用回転装置
AU2003204124B2 (en) * 2002-05-17 2005-03-24 Gebr. Kummerle Gmbh Arrowhead and Method of Attaching Same to an Arrow Shaft
JP2005330101A (ja) * 2004-04-20 2005-12-02 Sumitomo Heavy Ind Ltd マンコンベア駆動用減速機

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2488867A (en) * 1946-10-02 1949-11-22 Rolls Royce Nozzle-guide-vane assembly for gas turbine engines
US2918253A (en) * 1956-05-18 1959-12-22 Orenda Engines Ltd Rotor assemblies for turbines
JPS6081402A (ja) * 1983-10-13 1985-05-09 Toshiba Corp 蒸気タ−ビンのノズルダイアフラム支持装置
WO2006103152A1 (fr) * 2005-03-29 2006-10-05 Alstom Technology Ltd Procede et dispositif pour remplacer des pieces d'une machine hydraulique rotative
DE102005021446B3 (de) * 2005-05-04 2006-06-29 Technische Universität Dresden Gasturbine
WO2008012195A1 (fr) * 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2728130A1 (fr) * 2012-10-30 2014-05-07 Siemens Aktiengesellschaft Dispositif auxiliaire
WO2014067736A1 (fr) * 2012-10-30 2014-05-08 Siemens Aktiengesellschaft Dispositif d'assistance
US9920657B2 (en) 2012-10-30 2018-03-20 Siemens Aktiengesellschaft Aid device
EP3009604A1 (fr) * 2014-09-19 2016-04-20 United Technologies Corporation Système d'aubes fixes-variables fixées radialement
US11248538B2 (en) 2014-09-19 2022-02-15 Raytheon Technologies Corporation Radially fastened fixed-variable vane system

Also Published As

Publication number Publication date
CN101983280B (zh) 2014-03-05
CN101983280A (zh) 2011-03-02
JP2011516776A (ja) 2011-05-26
EP2257695A1 (fr) 2010-12-08
US20110103943A1 (en) 2011-05-05
US8708648B2 (en) 2014-04-29
JP5100886B2 (ja) 2012-12-19
WO2009121653A1 (fr) 2009-10-08

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