EP1462610A1 - Série d'aubes de rotor pour turbomachines - Google Patents

Série d'aubes de rotor pour turbomachines Download PDF

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Publication number
EP1462610A1
EP1462610A1 EP03007139A EP03007139A EP1462610A1 EP 1462610 A1 EP1462610 A1 EP 1462610A1 EP 03007139 A EP03007139 A EP 03007139A EP 03007139 A EP03007139 A EP 03007139A EP 1462610 A1 EP1462610 A1 EP 1462610A1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
row
support element
rotor
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Withdrawn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
EP03007139A
Other languages
German (de)
English (en)
Inventor
Christoph Dr. Richter
Heinrich Dr. Stüer
Frank Truckenmüller
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 EP03007139A priority Critical patent/EP1462610A1/fr
Priority to CNA2004100073600A priority patent/CN1534166A/zh
Priority to US10/797,376 priority patent/US20040191068A1/en
Priority to JP2004082078A priority patent/JP2004340131A/ja
Publication of EP1462610A1 publication Critical patent/EP1462610A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium

Definitions

  • the invention relates to an axial row of blades Turbines or a compressor.
  • Blade rows used which have a large inflow area exhibit.
  • the respective blades of such blade rows are comparatively long in their radial direction.
  • Such blades can be over one meter in length to reach.
  • the material titanium or titanium alloy has proven itself in this regard and is often used in steam turbine construction today.
  • the disadvantage here is the low internal damping of these blades.
  • the one made of titanium or titanium alloy guide manufactured blades of a row of blades undesirable vibrations in operation caused by suitable Measures must be dampened.
  • a proven measure is a coupling of the blades to one another, by the blade tips through so-called shrouds mechanically wedged together so that the Vibrations of blades about an axis that is radial extends from the blade root to the blade tip, diminishes become.
  • GB 2 105 414 support elements are presented, which in Blade tip area can be used.
  • tubular support elements between two blades in such a way arranged that the blade trailing edge of a blade with the blade leading edge of a next blade is mechanically connected.
  • the vibration of a blade has an influence on the vibration of a next blade.
  • the object of the present invention is the vibrations a blade in a blade row of a turbomachine to diminish.
  • the task is solved by a row of moving blades Turbomachine, the rotor blade row individual rotor blades has, each a blade root, a Blade center area, a blade tip and one Have leading edge and a trailing edge, the blade has cover plates on the blade tips, and between at least two adjacent blades in the middle of the blade a support element is attached in such a way that the support element the two adjacent blades couples with each other. Under the coupling of the neighboring Blades over the support element are any kind of Understand attachment. In other words: between two adjacent blades is in the middle of the blade a support element attached such that the two blades are attached to each other.
  • this support element is the small mass and the small spatial extent.
  • the low mass this support element leads to low centrifugal forces during of the company.
  • the manufacturing or assembly this support element is comparatively simple. Because of the low spatial expansion of this support element is achieved an aerodynamically advantageous behavior during operation.
  • leading edge a blade over the support element with the rear edge coupled to an adjacent blade.
  • a vibration of the blades are the amplitudes at the front or trailing edges largest.
  • a coupling of the front with the trailing edge leads to a particularly effective reduction the vibration amplitude.
  • the support element designed as a pin.
  • the Support elements for blades are used, which are made of the material Titanium or titanium alloy were manufactured.
  • Figure 1 is a partial cross section of a low pressure steam turbine 1 shown. Flows in via the inflow region 2 Flow medium through the flow channels 3, 4.
  • a rotatable mounted rotor 5 points from each other in the axial direction spaced different rows of blades, one of which for the sake of clarity, using only one blade row 6 is provided with a reference numeral 6.
  • the rotor 5 is rotated about an axis of rotation 10 moves.
  • FIG 2 there are two blades 11, 12 of a row of blades 6 shown.
  • the blades 11, 12 have one Blade root 13, a blade center region 14 and a blade tip 15 on.
  • the blades 11, 12 have furthermore a front edge 16 and a rear edge 17 on.
  • At the blade tips 15 are perpendicular to the radial Alignment 18 of the blades 11, 12 vertical cover plates 19 attached.
  • the radial alignment 18 is with the Arrow 18 shown.
  • the cover plates 19 are attached in such a way that the blade tips are perpendicular to the radial alignment 15 are towered over. Furthermore, they are Cover plates 19 from the front edge 16 to the rear edge 17 educated.
  • FIG. 3 shows a view of the cover plates 19, seen along the radial orientation 18.
  • the two dashed lines Lines 23 indicate a blade tip 15.
  • the two rotor blades 11, 12 are shown in FIG.
  • the direction of view is here as in Figure 3 along the radial alignment 18.
  • the representations of the cover plates 19 are omitted.
  • To see is a section through the blades 11, 12 in the blade center region 14.
  • a support element 24 is attached.
  • the support element 24 is connected to the leading edge 16 of the blade 12.
  • the Support element 24 can on the front and rear edge 16, 17th be fixed by welding or screwing. Further Possibilities for attaching the support element 24 to the The rear or front edge 16, 17 are in document GB 2 105 414 shown.
  • the blade feet 13 are not closer to that in FIG. 4 rotor 5 shown attached.
  • the support element 24 designed as a pen.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03007139A 2003-03-28 2003-03-28 Série d'aubes de rotor pour turbomachines Withdrawn EP1462610A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP03007139A EP1462610A1 (fr) 2003-03-28 2003-03-28 Série d'aubes de rotor pour turbomachines
CNA2004100073600A CN1534166A (zh) 2003-03-28 2004-03-01 涡轮机的动叶片组
US10/797,376 US20040191068A1 (en) 2003-03-28 2004-03-10 Moving-blade row for fluid-flow machines
JP2004082078A JP2004340131A (ja) 2003-03-28 2004-03-22 流体機械の動翼列

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03007139A EP1462610A1 (fr) 2003-03-28 2003-03-28 Série d'aubes de rotor pour turbomachines

Publications (1)

Publication Number Publication Date
EP1462610A1 true EP1462610A1 (fr) 2004-09-29

Family

ID=32798931

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03007139A Withdrawn EP1462610A1 (fr) 2003-03-28 2003-03-28 Série d'aubes de rotor pour turbomachines

Country Status (4)

Country Link
US (1) US20040191068A1 (fr)
EP (1) EP1462610A1 (fr)
JP (1) JP2004340131A (fr)
CN (1) CN1534166A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010033302A1 (de) * 2010-08-04 2012-02-09 Alstom Technology Ltd. Verfahren zum Überprüfen der Mechanischen Integrität von Stabilisierungselementen an den Laufschaufeln einer Turbine sowie Abtastvorrichtung zur Durchführung des Verfahrens
CN103470532A (zh) * 2013-08-23 2013-12-25 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压进口可转导叶片
CN103541926A (zh) * 2013-08-13 2014-01-29 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压首级可转导叶片

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1961918A1 (fr) * 2007-02-21 2008-08-27 ABB Turbo Systems AG Roue de turbine
FR2921099B1 (fr) * 2007-09-13 2013-12-06 Snecma Dispositif d'amortissement pour aube en materiau composite
EP2212548A4 (fr) * 2007-11-23 2011-02-23 Atlantis Resources Corp Pte Système de commande pour extraire de l'énergie électrique à partir d'un écoulement d'eau
CL2009000892A1 (es) * 2008-04-14 2010-03-05 Atlantis Resources Corporation Pte Ltd Aspa para accionar una maquina generadora de energia submarina, con una base, una punta, un borde anterior y uno posterior que se extienden desde la base hasta la punta, una cuerda de base, una cuerda de punta de aspa desplazada con respecto a la cuerda de base en un angulo de torsion entre 50 y 90 grados; maquina generadora.
AU2009238205B2 (en) 2008-04-14 2014-06-05 Atlantis Resources Corporation Pte Limited Central axis water turbine
US8052393B2 (en) * 2008-09-08 2011-11-08 General Electric Company Steam turbine rotating blade for a low pressure section of a steam turbine engine
DE102008059836A1 (de) 2008-12-01 2010-06-02 Alstom Technology Ltd. Strömungsmaschine, insbesondere Dampfturbine
EP2213837A1 (fr) 2009-01-29 2010-08-04 Siemens Aktiengesellschaft Système de pale de turbine
CA2760192A1 (fr) 2009-04-28 2010-11-04 Atlantis Resources Corporation Pte Limited Generateur de puissance sous-marine
AU2010312315B2 (en) 2009-10-27 2013-05-23 Atlantis Resources Corporation Pte Limited Underwater power generator
JP5558095B2 (ja) * 2009-12-28 2014-07-23 株式会社東芝 タービン動翼翼列および蒸気タービン
JP6124621B2 (ja) * 2013-02-28 2017-05-10 三菱日立パワーシステムズ株式会社 タービン動翼
CN104728170A (zh) * 2015-03-25 2015-06-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种压气机调频结构
ITUB20152313A1 (it) * 2015-07-20 2017-01-20 Nuovo Pignone Tecnologie Srl Girante senza contro-disco per turbomacchina a rigidita migliorata
EP3380704B1 (fr) 2016-01-12 2023-09-06 Siemens Energy Global GmbH & Co. KG Amortisseur flexible pour aubes de turbine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB440469A (en) * 1935-05-03 1935-12-31 Allis Chalmers Mfg Co Improvements in and relating to elastic-fluid turbine blades
US2278040A (en) * 1939-10-23 1942-03-31 Allis Chalmers Mfg Co Turbine blading
US2454115A (en) * 1945-04-02 1948-11-16 Allis Chalmers Mfg Co Turbine blading
CH272378A (de) * 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
GB696557A (en) * 1950-03-24 1953-09-02 Bbc Brown Boveri & Cie Vibration damper for the blades of elastic fluid turbines, compressors and the like
GB1037951A (en) * 1964-05-15 1966-08-03 Ass Elect Ind Improvements in or relating to rotor discs of axial-flow turbo-machines
GB1509185A (en) * 1975-08-04 1978-05-04 Reyrolle Parsons Ltd Fluid driven turbo machines
US4386887A (en) * 1980-06-30 1983-06-07 Southern California Edison Company Continuous harmonic shrouding
US5393200A (en) * 1994-04-04 1995-02-28 General Electric Co. Bucket for the last stage of turbine
EP0985801A2 (fr) * 1998-07-31 2000-03-15 Kabushiki Kaisha Toshiba Configuration des aubes pour turbines à vapeur
DE10108005A1 (de) * 2001-02-20 2002-08-22 Alstom Switzerland Ltd Bindung der Beschaufelung einer Strömungsmaschine

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US3778190A (en) * 1971-10-01 1973-12-11 Gen Electric Bucket cover attachment
DE3407946A1 (de) * 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur verhinderung der ausbreitung von titanfeuer bei turbomaschinen, insbesondere gasturbinen- bzw. gasturbinenstrahltriebwerken
DE4324960A1 (de) * 1993-07-24 1995-01-26 Mtu Muenchen Gmbh Laufrad einer Turbomaschine, insbesondere einer Turbine eines Gasturbinentriebwerks
JP3107266B2 (ja) * 1993-09-17 2000-11-06 株式会社日立製作所 流体機械および流体機械の翼装置
US5696323A (en) * 1996-06-25 1997-12-09 Alliedsignal, Inc. Two bar resonant beam Coriolis rate sensor
US5829956A (en) * 1997-04-22 1998-11-03 Chen; Yung Fan blade assembly
US6241471B1 (en) * 1999-08-26 2001-06-05 General Electric Co. Turbine bucket tip shroud reinforcement
GB2391270B (en) * 2002-07-26 2006-03-08 Rolls Royce Plc Turbomachine blade

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB440469A (en) * 1935-05-03 1935-12-31 Allis Chalmers Mfg Co Improvements in and relating to elastic-fluid turbine blades
US2278040A (en) * 1939-10-23 1942-03-31 Allis Chalmers Mfg Co Turbine blading
US2454115A (en) * 1945-04-02 1948-11-16 Allis Chalmers Mfg Co Turbine blading
CH272378A (de) * 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
GB696557A (en) * 1950-03-24 1953-09-02 Bbc Brown Boveri & Cie Vibration damper for the blades of elastic fluid turbines, compressors and the like
GB1037951A (en) * 1964-05-15 1966-08-03 Ass Elect Ind Improvements in or relating to rotor discs of axial-flow turbo-machines
GB1509185A (en) * 1975-08-04 1978-05-04 Reyrolle Parsons Ltd Fluid driven turbo machines
US4386887A (en) * 1980-06-30 1983-06-07 Southern California Edison Company Continuous harmonic shrouding
US5393200A (en) * 1994-04-04 1995-02-28 General Electric Co. Bucket for the last stage of turbine
EP0985801A2 (fr) * 1998-07-31 2000-03-15 Kabushiki Kaisha Toshiba Configuration des aubes pour turbines à vapeur
DE10108005A1 (de) * 2001-02-20 2002-08-22 Alstom Switzerland Ltd Bindung der Beschaufelung einer Strömungsmaschine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010033302A1 (de) * 2010-08-04 2012-02-09 Alstom Technology Ltd. Verfahren zum Überprüfen der Mechanischen Integrität von Stabilisierungselementen an den Laufschaufeln einer Turbine sowie Abtastvorrichtung zur Durchführung des Verfahrens
US8844360B2 (en) 2010-08-04 2014-09-30 Alstom Technology Ltd Method for checking the mechanical integrity of stabilizing elements on the rotor blades of a turbine and scanning device for implementing the method
CN103541926A (zh) * 2013-08-13 2014-01-29 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压首级可转导叶片
CN103541926B (zh) * 2013-08-13 2016-02-10 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压首级可转导叶片
CN103470532A (zh) * 2013-08-23 2013-12-25 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压进口可转导叶片
CN103470532B (zh) * 2013-08-23 2015-12-09 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的低压进口可转导叶片

Also Published As

Publication number Publication date
US20040191068A1 (en) 2004-09-30
JP2004340131A (ja) 2004-12-02
CN1534166A (zh) 2004-10-06

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