EP2322764A1 - Turbinenschaufelbefestigung für eine Strömungsmaschine - Google Patents

Turbinenschaufelbefestigung für eine Strömungsmaschine Download PDF

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Publication number
EP2322764A1
EP2322764A1 EP09014382A EP09014382A EP2322764A1 EP 2322764 A1 EP2322764 A1 EP 2322764A1 EP 09014382 A EP09014382 A EP 09014382A EP 09014382 A EP09014382 A EP 09014382A EP 2322764 A1 EP2322764 A1 EP 2322764A1
Authority
EP
European Patent Office
Prior art keywords
anchoring
tip
blade root
blade
teeth
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Withdrawn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
EP09014382A
Other languages
German (de)
English (en)
French (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
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 EP09014382A priority Critical patent/EP2322764A1/de
Priority to KR1020127012584A priority patent/KR20120107466A/ko
Priority to CN2010800521225A priority patent/CN102667065A/zh
Priority to PCT/EP2010/067582 priority patent/WO2011061193A1/de
Priority to US13/510,086 priority patent/US8926285B2/en
Priority to EP10782579.6A priority patent/EP2501902B1/de
Priority to RU2012124906/06A priority patent/RU2562687C2/ru
Priority to PL10782579T priority patent/PL2501902T3/pl
Priority to BR112012011802A priority patent/BR112012011802A2/pt
Priority to JP2012539306A priority patent/JP5680659B2/ja
Publication of EP2322764A1 publication Critical patent/EP2322764A1/de
Withdrawn legal-status Critical Current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
    • 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 is arranged in the blade groove, wherein the blade root comprises at least two anchoring teeth, 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 for this purpose comprises a plurality of turbine blades, which are shaped such that the thermal energy of the flow medium is converted into rotational energy of the rotor.
  • the flow medium is water vapor.
  • the turbomachines further include, besides the turbine blades arranged on the rotor, also turbine blades arranged on the housing.
  • the turbine blades disposed on the rotor are called turbine blades and the turbine blades disposed on the housing are turbine 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 blade root designs are known, namely the fir tree design and the dovetail design.
  • the cross-sectional contour of the blade root in Tannenbaumdesign has a front in the direction of rotation of the turbine blade and a region lying behind in the direction of rotation, which by a wavy 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 wavy contour corresponding to the blade root.
  • 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 mechanically heavily loaded. 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 object is to provide a Schaufelfußbefest Trent in which the crack growth of a crack is delayed.
  • a turbine blade attachment comprising a blade root and an airfoil and a blade groove, wherein the blade root is arranged in the blade groove (18), wherein the blade root comprises at least two anchoring teeth for installation in corresponding recesses in a rotor are formed, 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.
  • the height of the anchoring teeth here is to be understood as the spatial extent in the circumferential direction.
  • the anchoring teeth are formed in a wave-like contour. The height of the anchoring teeth varies in such a way that from anchor tooth to anchor tooth, the height to the blade root tip decreases, so that the last anchoring tooth at the blade root tip has the smallest height and the first anchoring tooth, which is arranged in the vicinity of the surface of the rotor, the largest Height.
  • the invention now starts from a completely different design, according to which the height now also varies from anchoring tooth to anchoring tooth, but the height of the anchoring teeth to the blade root tip increases.
  • the anchoring tooth arranged on the blade tip has the greatest height and the anchoring tooth closest to the rotor surface has the lowest height.
  • the anchoring teeth have an anchoring tooth tip, wherein the anchoring tooth tips are arranged substantially along a peak straight line.
  • the new design is characterized by a wavy contour, whereby the anchoring teeth represent a wave crest and between the anchoring teeth troughs are formed.
  • the anchoring teeth have an anchoring tooth tip at their tip with the anchoring tooth tips of the individual anchoring teeth arranged along the peak line.
  • an anchoring tooth tip is formed between the anchoring teeth, wherein the anchoring tooth tips are arranged substantially along a valley straight line. That is, the anchoring tooth tips, each disposed between the anchoring teeth, are arranged along an imaginary line lying on the valley straight line.
  • This design results in redundant voltage paths as soon as a crack occurs in the blade root.
  • the apex straight line with respect to the valley straight at an angle between 2 ° and 10 °, in particular between 1 ° and 12 °. In this angular range, 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 blade root tip.
  • the thus obtained Schaufelfußdesign thus has a plurality of anchoring teeth whose size increases from the rotor surface towards the Schaufelfußspitze.
  • the anchoring tooth between the anchoring tooth tip and the anchoring tooth tip on a flank, wherein between the anchoring tooth tip and the flank 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.
  • the forces should act as much as possible in the blade root so that crack growth is inhibited in the event of a crack.
  • mechanical stresses are high, so that according to the invention the outer notch radius is smaller 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 flank play on the anchoring tooth which is closest to the blade tip is minimal, that is to say that initially during installation at this point the anchoring tooth on the blade groove abuts and increase the airfoil clearance towards the blade.
  • FIG. 1 shows a section of a turbine blade, comprising a blade root 1 and an unspecified airfoil.
  • the blade root 1 according to FIG. 1 is executed in the so-called Christmas tree design and forms the state of the art.
  • Such a blade root 1 has an area 3 lying in the direction of rotation (arrow 2) and an area 4 lying in the direction of rotation.
  • 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 teeth 5 engage in a correspondingly contoured recess within a rotor, which is not shown in detail, whereby the turbine blade is attached via the blade root 1 on the rotor.
  • the in FIG. 1 illustrated blade root 1 is formed substantially symmetrically, that is, that in the front region 3 and in the rear region 4, the contour of the anchoring teeth 5 are formed 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 thus be described as wave-like, wherein an anchoring tooth tip 9 is arranged between each anchoring tooth tip 7.
  • the anchoring tooth tips 7 of the individual anchoring teeth 5 are in the in FIG. 1
  • the anchoring tooth tips 9 of the respective valleys between the anchoring teeth 5 lie in a line along a valley straight line 11.
  • 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 teeth 5 decreases to the blade root tip 12.
  • FIG. 2 1 shows a blade foot 1 designed according to the invention.
  • the rear region 4 could be designed correspondingly symmetrical.
  • illustrated blade root 1 according to the prior art is that the height H of the anchoring teeth 5 to the blade tip 12 increases towards.
  • the anchoring teeth 5 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 in FIG. 2 to see on a straight line.
  • the anchoring teeth may be corrugated as shown in FIG FIG. 1 is shown.
  • the height H is in accordance with the selected embodiment FIG. 2 approximately to the middle of the line on which the anchoring tooth tip 7 is arranged, determined 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 as a fir tree foot that in the FIG. 2 is not shown in detail, executed.
  • the anchoring tooth tips 7 rest on an anchoring tooth flank 15, which is formed essentially parallel to the tip straight line 10.
  • 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 lies between 2 ° and 10 ° with respect to one another.
  • an auxiliary straight line 16 is shown, which is arranged parallel to the peak straight line 10.
  • the angle ⁇ may have angles between 1 ° and 12 ° in alternative embodiments.
  • 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 determined according to FIG. 2 determined from the interface between the rising edge 6 and the valley line 11 and the interface of the descending edge 8 and the valley line 11. As in FIG. 2 can be seen, the length of the anchoring teeth 5 to the blade tip 12 towards.
  • the front transition region 13 and / or the rear transition region 14 may 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.
  • an edge 6 is formed between the anchoring tooth tip 9 and the anchoring tooth tip 7, between the Anank ceremoniesszahntalspitze 9 and the edge 6, an inner notch radius 16 is formed. Furthermore, an outer notch radius 17 is formed between the flank 6 and the anchoring tooth tip 7, wherein the outer notch radius 17 is smaller than the inner notch radius 16. This leads to optimal distributions of voltage paths. In the transition region 14 thus an outer notch radius 17 and inner notch radius 16 is formed, which is different according to the invention. In a first variant, the outer notch radius 17 is smaller than the inner notch radius 16. In a second variant, 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 increases from the anchoring tooth 5 to the anchoring tooth 5 towards the blade root tip 12.
  • 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 formed in alternative embodiments such that it decreases toward the blade root tip 12 from anchoring tooth 5 to anchoring tooth 5 back.
  • the outer notch radius 17 may be formed such that it decreases toward the blade root tip 12 from the anchoring tooth 5 to the anchoring tooth 5.
  • the blade root 1 is further designed such that the flank 6 rests against a support flank 20 corresponding in the blade groove 18. Between the flank 6 and the supporting flank 20, a supporting flank clearance 21, 22, 23 is thus formed.
  • the support flank play 21 is initially formed during installation of the blade root 1, such that the anchoring tooth 5, which is closest to the blade root tip 12, rests 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.
  • the backlash 22 and 23 are formed the same.
  • the backlash 23 is formed such that substantially no backlash 23 is present. This means that during installation of the anchoring tooth 5, which corresponds to the bearing ring clearance 23, rests. The flank play 22 and 21 increase toward the blade root 12 in this alternative embodiment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09014382A 2009-11-17 2009-11-17 Turbinenschaufelbefestigung für eine Strömungsmaschine Withdrawn EP2322764A1 (de)

Priority Applications (10)

Application Number Priority Date Filing Date Title
EP09014382A EP2322764A1 (de) 2009-11-17 2009-11-17 Turbinenschaufelbefestigung für eine Strömungsmaschine
KR1020127012584A KR20120107466A (ko) 2009-11-17 2010-11-16 터빈 엔진을 위한 터빈 블레이드 고정부
CN2010800521225A CN102667065A (zh) 2009-11-17 2010-11-16 用于涡轮机的涡轮叶片固定机构
PCT/EP2010/067582 WO2011061193A1 (de) 2009-11-17 2010-11-16 Turbinenschaufelbefestigung für eine strömungsmaschine
US13/510,086 US8926285B2 (en) 2009-11-17 2010-11-16 Turbine blade fastening for a turbomachine
EP10782579.6A EP2501902B1 (de) 2009-11-17 2010-11-16 Turbinenschaufelbefestigung für eine strömungsmaschine
RU2012124906/06A RU2562687C2 (ru) 2009-11-17 2010-11-16 Крепление турбинной лопатки для турбомашины
PL10782579T PL2501902T3 (pl) 2009-11-17 2010-11-16 Mocowanie łopatki turbiny w maszynie przepływowej
BR112012011802A BR112012011802A2 (pt) 2009-11-17 2010-11-16 fixação da pá de turbina para uma turbomáquina
JP2012539306A JP5680659B2 (ja) 2009-11-17 2010-11-16 タービンエンジン用のタービンブレード固定構造

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09014382A EP2322764A1 (de) 2009-11-17 2009-11-17 Turbinenschaufelbefestigung für eine Strömungsmaschine

Publications (1)

Publication Number Publication Date
EP2322764A1 true EP2322764A1 (de) 2011-05-18

Family

ID=42044744

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09014382A Withdrawn EP2322764A1 (de) 2009-11-17 2009-11-17 Turbinenschaufelbefestigung für eine Strömungsmaschine
EP10782579.6A Not-in-force EP2501902B1 (de) 2009-11-17 2010-11-16 Turbinenschaufelbefestigung für eine strömungsmaschine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10782579.6A Not-in-force EP2501902B1 (de) 2009-11-17 2010-11-16 Turbinenschaufelbefestigung für eine strömungsmaschine

Country Status (9)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3045664A1 (de) * 2015-01-16 2016-07-20 Siemens Aktiengesellschaft Laufschaufelbefestigung für eine thermische Strömungsmaschine
WO2019120885A1 (de) 2017-12-22 2019-06-27 Siemens Aktiengesellschaft Verfahren zum messen eines tannenbaumförmigen schaufelfusses, messvorrichtung sowie system umfassend eine solche

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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.
DE2512347A1 (de) * 1974-03-25 1975-10-09 Theodore George John Norbut Turbinenlaeufer
US5160242A (en) * 1991-05-31 1992-11-03 Westinghouse Electric Corp. Freestanding mixed tuned steam turbine blade
EP1905954A1 (de) * 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Turbinenschaufel

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Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH240283A (de) * 1944-03-25 1945-12-15 Sulzer Ag Turbomaschine.
DE2512347A1 (de) * 1974-03-25 1975-10-09 Theodore George John Norbut Turbinenlaeufer
US5160242A (en) * 1991-05-31 1992-11-03 Westinghouse Electric Corp. Freestanding mixed tuned steam turbine blade
EP1905954A1 (de) * 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Turbinenschaufel

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3045664A1 (de) * 2015-01-16 2016-07-20 Siemens Aktiengesellschaft Laufschaufelbefestigung für eine thermische Strömungsmaschine
WO2019120885A1 (de) 2017-12-22 2019-06-27 Siemens Aktiengesellschaft Verfahren zum messen eines tannenbaumförmigen schaufelfusses, messvorrichtung sowie system umfassend eine solche
DE102017223711A1 (de) 2017-12-22 2019-06-27 Siemens Aktiengesellschaft Verfahren zum Messen eines tannenbaumförmigen Schaufelfußes, Messvorrichtung sowie System umfassend eine solche

Also Published As

Publication number Publication date
JP5680659B2 (ja) 2015-03-04
EP2501902A1 (de) 2012-09-26
KR20120107466A (ko) 2012-10-02
PL2501902T3 (pl) 2017-12-29
EP2501902B1 (de) 2017-05-17
RU2012124906A (ru) 2013-12-27
US8926285B2 (en) 2015-01-06
US20120224971A1 (en) 2012-09-06
WO2011061193A1 (de) 2011-05-26
RU2562687C2 (ru) 2015-09-10
BR112012011802A2 (pt) 2019-09-24
CN102667065A (zh) 2012-09-12
JP2013510995A (ja) 2013-03-28

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