EP2501902A1 - Fixation d'ailette de turbine pour une machine d'écoulement - Google Patents

Fixation d'ailette de turbine pour une machine d'écoulement

Info

Publication number
EP2501902A1
EP2501902A1 EP10782579A EP10782579A EP2501902A1 EP 2501902 A1 EP2501902 A1 EP 2501902A1 EP 10782579 A EP10782579 A EP 10782579A EP 10782579 A EP10782579 A EP 10782579A EP 2501902 A1 EP2501902 A1 EP 2501902A1
Authority
EP
European Patent Office
Prior art keywords
anchoring
blade
tip
blade root
turbine blade
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.)
Granted
Application number
EP10782579A
Other languages
German (de)
English (en)
Other versions
EP2501902B1 (fr
Inventor
Christoph Hermann Richter
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
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 PL10782579T priority Critical patent/PL2501902T3/pl
Priority to EP10782579.6A priority patent/EP2501902B1/fr
Publication of EP2501902A1 publication Critical patent/EP2501902A1/fr
Application granted granted Critical
Publication of EP2501902B1 publication Critical patent/EP2501902B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/12—Blades
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to a turbine blade attachment comprising a blade root and an airfoil and a blade groove, wherein the blade root in the blade groove
  • blade root at least two
  • Anchoring teeth comprises, which are designed for installation in corresponding recesses in a rotor.
  • turbomachines in particular steam turbines, the energy of a flow medium is converted into rotational energy of a rotor.
  • the rotor comprises for this purpose several Turbi ⁇ nenschaufeln which are shaped in such a way that the thermal energy of the flowing medium is converted into rotational energy of the rotor.
  • the flow medium is water vapor.
  • the flow machines further comprise next to the positioned on the rotor turbine blades and the housing at ⁇ parent turbine blades.
  • the turbine blades arranged on the rotor are called turbine blades and the turbine blades arranged on the housing are turbine guide vanes.
  • the turbine blades have blade roots that attach the turbine blades to the rotor.
  • the blade roots are designed such that they engage in corresponding recesses within the rotor.
  • the inner contour of the recess corresponds to the outer contour of the blade roots.
  • two actors ⁇ felfußdesigns are known, namely the Christmas tree design and dovetail design.
  • the cross-sectional contour of the blade root in the Christmas tree design has a forward region in the direction of rotation of the turbine blade and a region lying behind in the direction of rotation, which has a wave-shaped contour is marked.
  • the elevations of such a wavy contour form multiple anchoring teeth in the two areas.
  • the turbine blades are inserted with the blade roots in corresponding recesses within the rotor.
  • the rotor has a blade root corres ⁇ -chief, undulating contour.
  • the rotor with the turbine blades rotates in operation at a comparatively high frequency of, for example 50 Hz or 60 Hz. It is also known that steam turbines are operated for corresponding applications at higher speeds. The high temperatures and speeds that occur during operation result in enormous thermal and mechanical loads. In particular, the blade roots of the turbine blades are subject to high mechanical loading. It is possible that the oscillations in the turbine blades that occur during operation that are transmitted to the blade roots may result in cracks in the turbine blade roots or in the corresponding recesses in the rotor.
  • the invention begins, whose task is to provide a Schaufelfußbefestist in which the
  • a turbine blade attachment comprising a blade root and an airfoil and a blade groove, the blade root being disposed in the blade groove, the blade root comprises at least two anchoring teeth, which are designed for installation in corresponding recesses in a rotor, wherein the height of the anchoring teeth increases toward the blade root tip.
  • the invention is based on the idea to move away from the known blade foot design for pine tree feet.
  • the anchoring teeth are formed so that the height of the anchoring teeth decreases towards the blade root tip. Under the height of the anchoring teeth here is the
  • the United ⁇ anchoring teeth are formed in a wave-like contour.
  • the height of the anchoring teeth varies in this case in such a way that the height of the blade ⁇ toe out of abutment tooth to anchoring tooth decreases, so that the final anchoring tooth having the smallest height at the Schaufelfußspitze and the first anchoring tooth which is arranged in the vicinity of the surface of the rotor, has the greatest height.
  • the invention starts from a completely different design from what is now the height also varied to be of approximately ⁇ anchoring tooth to anchoring tooth, but the height of the teeth increases towards the anchoring Schaufelfußspitze. This means that the arranged at the blade tip anchoring ⁇ approximately tooth the greatest height and lying on the rotor surface closest anchoring tooth has the lowest height ⁇ .
  • the anchoring ⁇ teeth have an anchoring tooth tip, the tooth tips anchoring ⁇ approximately along a tip Gera ⁇ are arranged substantially.
  • the new design is characterized by a wave-shaped contour, said anchoring teeth quasi a wave crest illustrate ⁇ and are formed between the anchoring teeth troughs of ⁇ .
  • the anchoring teeth have at their tip an anchoring tooth tip, wherein the anchoring tooth ⁇ tips of the individual anchoring teeth along the peak straight lines are arranged.
  • each a Verank fürszahntalspitze is formed between the anchoring teeth, the Verank ceremoniesszahntalspitzen in Wesent ⁇ union disposed along a valley line.
  • This design means that redundant power paths are ent ⁇ when a crack is formed in the blade root.
  • the stress distribution during operation is optimal.
  • the length of the anchoring teeth increases towards the blade tip.
  • the length of the anchoring teeth is varied so that the length increases to the blade root tip.
  • the length of the anchoring teeth usually decreases towards the tip of the foot.
  • Anchoring tooth between the anchoring tooth tip and the anchoring tooth tip on a flank, wherein between the anchoring tooth tip and the edge of an inner notch radius and between the flank and the
  • Anchoring tooth tip an outer notch radius is formed, wherein the outer notch radius is greater than the inner notch radius.
  • a bearing flank play is formed between the flank and a bearing flank corresponding in the blade groove, wherein the
  • the blade root tip next to it is minimal, which means that initially at installation at this point the
  • Anchoring tooth rests against the blade groove and the
  • FIG. 1 is a Schaufelfußdesign according to the prior art
  • FIG. 2 shows a blade root attachment according to the invention.
  • FIG. 1 shows a detail of a turbine blade, comprising a blade root 1 and a blade leaf, not illustrated in more detail.
  • the blade 1 according to Figure 1 is carried out in the so-called Christmas tree design ⁇ and forms the prior art.
  • Such a blade 1 has a rotationally Rich ⁇ device (arrow 2) lying in front region 3 and a rear in the direction of rotation region 4.
  • the blade root 1 according to FIG. 1 has three anchoring teeth 5 both in the front region 3 and in the rear region 4.
  • the anchoring ⁇ approximately teeth 5 engage in a correspondingly contoured Ausneh ⁇ mung an inside of a rotor, which is not shown in detail, so that the turbine blade is mounted on the blade 1 to the rotor.
  • the blade root 1 shown in FIG. 1 is substantially symmetrical, ie, in the front region 3 and in the rear region 4, the contour of the anchoring teeth 5 are substantially identical.
  • the anchoring ⁇ teeth 5 are designed for installation in corresponding recesses in a rotor.
  • Each anchoring tooth 5 has a height H.
  • the anchoring tooth 5 has a rising flank 6, an anchoring tooth tip 7 and a descending flank 8.
  • the contour of the blade root 1 can be described as waves thus, a Verank mecanics leopardtalspitze 9 is disposed between each anchoring ⁇ approximately tooth tip.
  • the anchoring tooth tips 7 of the individual anchoring approximately teeth 5 are chosen in Figure 1 as in a line on a tip line 10. On the other hand lie ⁇ gen the Verank ceremoniess leopardtalspitzen 9 of the respective valleys between the anchoring teeth 5 on a line along a valley line 11th
  • the height H of an anchoring tooth 5 can be determined in a first approximation as follows: The shortest distance between the anchoring tooth tip 7 and the valley straight line 11. According to the prior art, the height H of the anchoring takes approximately ⁇ teeth from 5 to Schaufelfußspitze 12th
  • FIG. 2 shows a Schau- embodying the present invention feifuß 1. only the Kon ⁇ structure of the blade root 1 in the front region 3 the sake of clarity is shown.
  • the rear region 4 could be correspondingly symmetrical ⁇ forms.
  • the difference from the blade root 1 according to the prior art shown in FIG. 1 is inter alia that the height H of the anchoring teeth 5 increases towards the blade tip 12.
  • the shape of the anchoring teeth 5 shown in Figure 2 is designed substantially trapezoidal, that is, that the rising edge 6 and the descending edge 8 is designed as a straight line.
  • the anchoring tooth tip 7 and the anchoring tooth tip 9 lie, as can be seen in FIG. 2, on a straight line.
  • the anchoring teeth may be wavy, as shown in FIG.
  • the height H is determined in the selected Ausure ⁇ approximately example according to Figure 2 approximately from the center of Gera ⁇ den, on which the anchoring tooth tip 7 is arranged to the valley straight line 11.
  • the height H could just as well be determined in a front transition area 13 or from the rear transition area 14 to the valley straight line 11.
  • the blade root 1 according to FIG. 2 is designed as a fir tree root, which is not shown in greater detail in FIG.
  • the Ver ⁇ anchoring tooth tip 7 lie on a Verank réelles leopard- edge 15 which is substantially parallel to the tips of straight
  • the anchoring tooth flanks 15 lie on the peak straight line 10.
  • the valley straight line 11 and the pointed straight line 10 are arranged at an angle which is between 2 ° and 10 ° with respect to one another.
  • an auxiliary straight line 30, which is arranged parallel to the straight line 10 is shown in FIG.
  • the angle ⁇ may have angles between 1 ° and 12 ° in alternative embodiments.
  • the Blade foot 1 has an end-side blade end 12 which is formed relative to a rotation axis of the rotor 19.
  • the blade root 1 has at least two along one of the
  • the length L of the anchoring teeth 5 to the blade tip 12 is also varied.
  • the length L of the anchoring tooth 5 is shown in Figure 2 from the interface between the rising edge 6 and
  • Tal straight line 11 and the interface of the descending edge 8 and the valley line 11 determined. As can be seen in Figure 2, taking the length of the anchoring teeth 5 to the vane tip 12 towards.
  • the front transition area 13 and / or the rear About ⁇ transition region 14 can be rounded by radii.
  • the blade root 1 is fitted in a rotor 19 in a blade groove 18. This means that the edge 6 of the respective anchoring teeth 5 rests against a support flank 20.
  • Anchoring tooth tip 7 is an edge 6 is formed.
  • an inner notch radius 16 is formed between the Anank fürs leopardtalspitze 9 and the edge 6, an inner notch radius 16 is formed. Furthermore, between the flank 6 and the anchoring tooth tip 7, an outer notch radius 17 is formed, wherein the outer
  • Notch radius 17 is smaller than the inner notch radius 16. This leads to optimal distributions of voltage paths.
  • Transition region 14 is thus formed an outer notch radius 17 and inner notch radius 16, which is different according to the invention.
  • the outer notch radius 17 is smaller than the inner notch radius 16.
  • the outer notch radius 17 may be greater than the inner notch radius 16.
  • the outer notch radius 17 is such that it increases towards the blade tip 12. This means that the outer notch radius 17 of anchoring tooth 5 to
  • Anchoring tooth 5 to the blade root tip 12 increases toward.
  • the inner notch radius 16 is formed such that it increases toward the blade root tip 12 of the anchoring tooth 5 to the anchoring tooth 5 out.
  • the inner notch radius 16 may be in alternative
  • Embodiments should be designed such that it is towards the blade root tip 12 from anchoring tooth 5 to
  • Anchoring tooth 5 decreases towards. Likewise, in a
  • the outer notch radius 17 may be formed such that it decreases towards the blade root tip 12 from anchoring tooth 5 to anchoring tooth 5.
  • the blade root 1 is further designed such that the flank 6 at one in the blade groove 18th
  • Anchoring tooth 5 which is the blade root tip 12 closest, abuts directly on the support flank 20. This means that a contact between the flank 6 and the supporting flank 20 is present.
  • the blade root 1 is formed such that the backlash 22 and 23, are larger. This means that from the blade root tip 12, the backlash plays 22 and 23 of the anchoring teeth 5 formed towards the airfoil increase.
  • Support flange games 22 and 23 formed the same.
  • Supporting backlash 23 designed such that substantially no backlash 23 is present. It means that during installation of the anchoring tooth 5, which corresponds to the backlash 23, rests. The flank play 22 and 21 increase toward the blade root 12 in this alternative embodiment.
  • the anchoring tooth 5 which is the backlash 22

Landscapes

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

Abstract

L'invention concerne une fixation d'ailette de turbine, comprenant une embase d'ailette (1) conçue dans le design de pied de sapin, qui présente des dents d'ancrage (5), qui sont conçues en direction de la pointe en fonte d'ailette (12), de telle sorte que la hauteur (H) des dents d'ancrage (5) augmente en direction de la pointe en fonte d'ailette (12).
EP10782579.6A 2009-11-17 2010-11-16 Fixation d'aubes de turbines pour une turbomachine Not-in-force EP2501902B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL10782579T PL2501902T3 (pl) 2009-11-17 2010-11-16 Mocowanie łopatki turbiny w maszynie przepływowej
EP10782579.6A EP2501902B1 (fr) 2009-11-17 2010-11-16 Fixation d'aubes de turbines pour une turbomachine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09014382A EP2322764A1 (fr) 2009-11-17 2009-11-17 Fixation d'aubes de turbines pour une turbomachine
PCT/EP2010/067582 WO2011061193A1 (fr) 2009-11-17 2010-11-16 Fixation d'ailette de turbine pour une machine d'écoulement
EP10782579.6A EP2501902B1 (fr) 2009-11-17 2010-11-16 Fixation d'aubes de turbines pour une turbomachine

Publications (2)

Publication Number Publication Date
EP2501902A1 true EP2501902A1 (fr) 2012-09-26
EP2501902B1 EP2501902B1 (fr) 2017-05-17

Family

ID=42044744

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09014382A Withdrawn EP2322764A1 (fr) 2009-11-17 2009-11-17 Fixation d'aubes de turbines pour une turbomachine
EP10782579.6A Not-in-force EP2501902B1 (fr) 2009-11-17 2010-11-16 Fixation d'aubes de turbines pour une turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09014382A Withdrawn EP2322764A1 (fr) 2009-11-17 2009-11-17 Fixation d'aubes de turbines pour une turbomachine

Country Status (9)

Country Link
US (1) US8926285B2 (fr)
EP (2) EP2322764A1 (fr)
JP (1) JP5680659B2 (fr)
KR (1) KR20120107466A (fr)
CN (1) CN102667065A (fr)
BR (1) BR112012011802A2 (fr)
PL (1) PL2501902T3 (fr)
RU (1) RU2562687C2 (fr)
WO (1) WO2011061193A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3045664A1 (fr) * 2015-01-16 2016-07-20 Siemens Aktiengesellschaft Fixation d'aube pour turbomachine thermique
DE102017223711A1 (de) 2017-12-22 2019-06-27 Siemens Aktiengesellschaft Verfahren zum Messen eines tannenbaumförmigen Schaufelfußes, Messvorrichtung sowie System umfassend eine solche
JP7163523B1 (ja) * 2022-03-24 2022-10-31 三菱重工業株式会社 タービン動翼、タービン動翼組立体、ガスタービン及びガスタービンの補修方法

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CH240283A (de) * 1944-03-25 1945-12-15 Sulzer Ag Turbomaschine.
GB677142A (en) * 1949-08-24 1952-08-13 Power Jets Res & Dev Ltd Improved mounting for turbine and like blades
US3079681A (en) * 1956-01-18 1963-03-05 Fentiman & Sons Ltd F Method of making a joint
US3891351A (en) * 1974-03-25 1975-06-24 Theodore J Norbut Turbine disc
JPS62271903A (ja) * 1986-05-21 1987-11-26 Mitsubishi Heavy Ind Ltd タ−ビン翼
US4824328A (en) * 1987-05-22 1989-04-25 Westinghouse Electric Corp. Turbine blade attachment
GB2238581B (en) * 1989-11-30 1994-01-12 Rolls Royce Plc Improved attachment of a gas turbine engine blade to a turbine rotor disc
US5147180A (en) * 1991-03-21 1992-09-15 Westinghouse Electric Corp. Optimized blade root profile for steam turbine blades
US5160242A (en) * 1991-05-31 1992-11-03 Westinghouse Electric Corp. Freestanding mixed tuned steam turbine blade
DE4324960A1 (de) * 1993-07-24 1995-01-26 Mtu Muenchen Gmbh Laufrad einer Turbomaschine, insbesondere einer Turbine eines Gasturbinentriebwerks
US5431543A (en) * 1994-05-02 1995-07-11 Westinghouse Elec Corp. Turbine blade locking assembly
JP3182603B2 (ja) 1995-04-26 2001-07-03 株式会社日立製作所 アルミニウム合金の接合方法及びアルミニウム合金製真空容器
US6321502B1 (en) * 1999-06-16 2001-11-27 Geometrica, Inc. Method of making connector hub
US6435833B1 (en) * 2001-01-31 2002-08-20 General Electric Company Bucket and wheel dovetail connection for turbine rotors
ITMI20011970A1 (it) * 2001-09-21 2003-03-21 Nuovo Pignone Spa Connessione migliorata di palette su di un disco rotorico di una turbina a gas
CN2809222Y (zh) * 2005-07-31 2006-08-23 东方汽轮机厂 汽轮机大承载枞树型叶根及轮槽结构
EP1905954A1 (fr) * 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Aube de turbine
CN201103424Y (zh) * 2007-12-03 2008-08-20 哈尔滨汽轮机厂有限责任公司 一种大型全转速汽轮机中压缸叶片使用的纵树型p叶根

Also Published As

Publication number Publication date
BR112012011802A2 (pt) 2019-09-24
US8926285B2 (en) 2015-01-06
EP2322764A1 (fr) 2011-05-18
EP2501902B1 (fr) 2017-05-17
RU2012124906A (ru) 2013-12-27
RU2562687C2 (ru) 2015-09-10
JP5680659B2 (ja) 2015-03-04
CN102667065A (zh) 2012-09-12
US20120224971A1 (en) 2012-09-06
JP2013510995A (ja) 2013-03-28
WO2011061193A1 (fr) 2011-05-26
KR20120107466A (ko) 2012-10-02
PL2501902T3 (pl) 2017-12-29

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