EP2218875A1 - Bandage d'aube dans une turbomachine - Google Patents

Bandage d'aube dans une turbomachine Download PDF

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Publication number
EP2218875A1
EP2218875A1 EP09002224A EP09002224A EP2218875A1 EP 2218875 A1 EP2218875 A1 EP 2218875A1 EP 09002224 A EP09002224 A EP 09002224A EP 09002224 A EP09002224 A EP 09002224A EP 2218875 A1 EP2218875 A1 EP 2218875A1
Authority
EP
European Patent Office
Prior art keywords
blade
coupling element
shroud
arrangement according
tip
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Withdrawn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
EP09002224A
Other languages
German (de)
English (en)
Inventor
Christoph Hermann Dr. 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 EP09002224A priority Critical patent/EP2218875A1/fr
Priority to PCT/EP2010/050936 priority patent/WO2010094540A1/fr
Priority to EP10702854A priority patent/EP2399005B1/fr
Priority to US13/201,893 priority patent/US20110299989A1/en
Priority to CN2010800081780A priority patent/CN102317578A/zh
Publication of EP2218875A1 publication Critical patent/EP2218875A1/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Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the invention relates to an arrangement comprising a first blade and a second blade arranged adjacent to the first blade.
  • turbomachines are, for example, compressors, gas turbines or steam turbines.
  • the aforementioned turbomachines have in common that they consist of a housing and a rotor rotatably mounted in the housing, wherein between the rotor and the housing, a flow channel is formed, through which a flow medium flows.
  • the flow medium is steam in steam turbines.
  • vibration excitations Another problem of the vibration excitations is that the blades cause vibrations due to the vibration excitations, which lead to material fatigue of both the turbine blade and the rotor claw, in which the turbine blade is arranged. It would be desirable to achieve a reduction of the vibration amplitudes, which leads to a reduction of the material stress.
  • This object is achieved by an arrangement comprising a first blade and a second blade arranged adjacent to the first blade, wherein a coupling element is fixedly arranged in the first blade and a part of the coupling element bears against the second blade.
  • nodal diameter vibrations form.
  • These node diameter vibrations are characterized in that the amplitudes of the oscillations have a sinusoidal shape over the circumference of the blades.
  • An advantage of the invention is that such relative rotations of the immediate or distant neighboring blades are in accordance with the invention be steamed.
  • adjacent blades are modified such that a subset of the blades receives a coupling element which is firmly connected to the blade. This coupling element is designed such that it bears against the next adjacent blade or even up to the next but one neighboring blade, but is not firmly connected to the adjacent blade.
  • the first blade has a first blade tip and the second blade has a second blade tip, wherein the coupling element is arranged in the region of the first and second blade tip.
  • the vibrations are the largest due to the design of the blade tips. Therefore, it is advantageous if the damping device is arranged in the blade tip.
  • the coupling element is therefore advantageously arranged in the region of the first and second blade tip. The amplitudes of the disturbing vibrations are greatest there and are therefore most effectively damped.
  • the first blade tip on a first shroud wherein the coupling element is fixedly arranged in the first shroud.
  • the arrangement of a coupling element which is basically a foreign element, a suitable location must be found where the coupling element can be arranged.
  • the shrouds are arranged on the blade tips and have a construction which is comparatively large to the overall blade. In this shroud, the coupling element is fixed. This can be done for example by a soldering, a screw or riveting.
  • the second blade tip which belongs to the adjacent blade, a second shroud, wherein the coupling element is arranged in the second shroud.
  • the coupling element in the second shroud is loosely arranged, d. H. not firmly connected to the second shroud.
  • the second shroud is in this case arranged such that a centrifugal force occurring during operation leads to the coupling element being pressed against the second shroud. This means that the coupling element rubs in the second shroud when an oscillation occurs. This results in an energy dissipation, whereby the vibration is damped.
  • the first shroud and the second shroud each have a slot in which the coupling element is arranged.
  • a slot With a slot, a comparatively simple and production-technically favorable solution is available in order to effectively arrange the coupling element in the shroud.
  • the slot is arranged laterally in the first shroud and in the second shroud. Due to the lateral arrangement, it is possible to easily remove the coupling element during revision work.
  • the coupling element is elongated and narrow.
  • the effective damping of the blade vibrations depends essentially on the shape and the material of the coupling element. The longer the coupling element, the greater the oscillation amplitudes of the tip of the coupling element. The longer the coupling element is, the greater are therefore the vibration amplitudes at the top.
  • the material should be chosen such that it can be connected as rigidly and firmly as possible with the blade, the strength values of the coupling element should be such that the coupling element itself can hardly perform their own vibrations.
  • the coupling element is designed as a sheet metal.
  • the sheet has a rectangular shape with a width L and a height H, with the proviso that L is greater than H and that the coupling element is arranged in the shroud, that the surface with the width L in operation rests against the shroud ,
  • the coupling element therefore has the shape of a flat blade.
  • the coupling element is in a radial direction, i. H. in the direction in which the centrifugal forces prevail, relatively easily bendable, which results in that the coupling element can be easily pressed against the other shroud.
  • a bend in the axial direction, d. H. hardly possible perpendicular to the centrifugal force direction. This means that the vibration of the blade, on which the coupling element is fixed, entrains sufficiently well. Effective damping is possible.
  • the FIG. 1 shows a section of an arrangement in the radial direction. D. h., The radial direction is perpendicular to Plane.
  • the arrangement comprises a first blade 1 and a second blade 2 arranged adjacent to the first blade 1.
  • the first blade 1 and the second blade 2 are fixedly arranged on a rotor (not illustrated) via rotor claws.
  • the rotor rotates about a rotation axis 3.
  • the first blade 1 and the second blade 2 are elongated in the radial direction and are flowed during operation via a flow medium, not shown, wherein the first blade 1 and the second blade 2 rotation in a rotational direction 4 leads.
  • the first blade 1 is arranged adjacent to the second blade 2.
  • the first blade 1 comprises a coupling element 5, which is fixedly connected in a manner not shown with the first blade 1.
  • the coupling element 5 can be firmly connected, for example by screwing, riveting or by soldering to the first blade 1.
  • An oscillation 6 of the first blade 1 leads to a vibration of the coupling element tip 7.
  • This harmonic oscillation 8 is minimized, which takes place in that the coupling element 5 rests against the second blade 2 .
  • a free end 9 of the coupling element 5, which is arranged outside the first blade 1 is pressed in the radial direction outwards against the second blade 2. This leads to a friction between the free end 9 of the coupling element 5 and the second blade. 2
  • the coupling element 5 is arranged in a blade tip of the first blade 1 and in a blade tip of the second blade 2, which in the FIG. 1 not shown in detail.
  • FIG. 3 shows a shroud 10 of the first and second blades 1 and 2, respectively.
  • the shroud 10 is hereby arranged on the blade tip of the first blade 1 or second blade 2.
  • the shroud 10 has slots 11 into which the coupling element 5 is arranged.
  • the coupling element 5 is fixedly arranged in the slot 11.
  • the coupling element 5 is arranged only loosely in the slot 11. An occurring during operation centrifugal force acts in the centrifugal force direction 12, which is identical to the radial direction.
  • the FIG. 2 shows an alternative representation of a part of an arrangement.
  • the first blade 1 has a first shroud 13 and the blade 2 has a second shroud 14.
  • the shrouds are arranged in the blade tip of the first blade 1 and the second blade 2.
  • the coupling element 5 is arranged laterally in the first shroud 13 and in the second shroud 14.
  • the coupling element 5 is elongated and narrow and designed as a sheet metal.
  • the coupling element 5 has seen in cross section a rectangular shape with a width L and a height H.
  • the height H is substantially identical to the height H of the slot 11. At least the height H of the sheet 5 should be slightly smaller than the height H of the slot 11.
  • L is greater than H and that the coupling element 5 in the Shroud 14 is arranged so that the surface with the width L in operation rests on the shroud 14. As a result, a friction will result, which leads to an energy dissipation and thus causes a vibration reduction.
  • the coupling element 5 is fixedly arranged with the first shroud 13, which can be done for example by a screw.
  • screws are used, which connects the coupling element 5 with the first blade 1 fixed. This results in screw 15, 16.
  • the screw 15, 16 may be oriented, for example, in the axial direction 17. Of course, the screw connection 15, 16 can also take place in the radial direction 18.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09002224A 2009-02-17 2009-02-17 Bandage d'aube dans une turbomachine Withdrawn EP2218875A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09002224A EP2218875A1 (fr) 2009-02-17 2009-02-17 Bandage d'aube dans une turbomachine
PCT/EP2010/050936 WO2010094540A1 (fr) 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine
EP10702854A EP2399005B1 (fr) 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine
US13/201,893 US20110299989A1 (en) 2009-02-17 2010-01-27 Blade union of a turbo machine
CN2010800081780A CN102317578A (zh) 2009-02-17 2010-01-27 涡轮机的叶片组合体

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09002224A EP2218875A1 (fr) 2009-02-17 2009-02-17 Bandage d'aube dans une turbomachine

Publications (1)

Publication Number Publication Date
EP2218875A1 true EP2218875A1 (fr) 2010-08-18

Family

ID=40874982

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09002224A Withdrawn EP2218875A1 (fr) 2009-02-17 2009-02-17 Bandage d'aube dans une turbomachine
EP10702854A Not-in-force EP2399005B1 (fr) 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10702854A Not-in-force EP2399005B1 (fr) 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine

Country Status (4)

Country Link
US (1) US20110299989A1 (fr)
EP (2) EP2218875A1 (fr)
CN (1) CN102317578A (fr)
WO (1) WO2010094540A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8951013B2 (en) * 2011-10-24 2015-02-10 United Technologies Corporation Turbine blade rail damper
US8967973B2 (en) * 2011-10-26 2015-03-03 General Electric Company Turbine bucket platform shaping for gas temperature control and related method
CN109057870B (zh) * 2018-08-07 2020-12-01 中国航发湖南动力机械研究所 涡轮叶片组
US11719440B2 (en) * 2018-12-19 2023-08-08 Doosan Enerbility Co., Ltd. Pre-swirler having dimples

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
US1618285A (en) * 1927-02-22 Blade lashing
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.
DE1551180A1 (de) * 1965-12-06 1969-06-19 Gen Electric Leitschaufelkranz fuer Turbomaschinen,insbesondere Gasturbinen-Triebwerke
US4191508A (en) * 1977-02-02 1980-03-04 Hitachi, Ltd. Turbine rotor construction
DE69704001D1 (de) 1996-05-09 2001-03-08 Rolls Royce Plc Dämpfungsstifte für Deckbänder von Turbomaschinen
DE10256778A1 (de) 2001-12-11 2004-01-08 Alstom (Switzerland) Ltd. Schwingungsdämpfer
JP2008045419A (ja) * 2006-08-11 2008-02-28 Mitsubishi Heavy Ind Ltd インテグラルシュラウド翼のせん断応力低減構造
EP2019188A1 (fr) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Etage de rotor comprenant un dispositif d'amortissement

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
GB695724A (en) * 1950-08-01 1953-08-19 Rolls Royce Improvements in or relating to structural elements for axial-flow turbo-machines such as compressors or turbines of gas-turbine engines
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
GB1195012A (en) * 1966-06-21 1970-06-17 Rolls Royce Rotor for Bladed Fluid Flow Machines.
US3986792A (en) * 1975-03-03 1976-10-19 Westinghouse Electric Corporation Vibration dampening device disposed on a shroud member for a twisted turbine blade
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US4784571A (en) * 1987-02-09 1988-11-15 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
FR2612249B1 (fr) * 1987-03-12 1992-02-07 Alsthom Aubage mobile pour turbines a vapeur
JPH08303205A (ja) * 1995-05-11 1996-11-19 Hitachi Ltd タービン動翼
US5645402A (en) * 1996-04-10 1997-07-08 Solar Turbines Incorporated Turbine blade vibration dampening
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1618285A (en) * 1927-02-22 Blade lashing
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
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.
DE1551180A1 (de) * 1965-12-06 1969-06-19 Gen Electric Leitschaufelkranz fuer Turbomaschinen,insbesondere Gasturbinen-Triebwerke
US4191508A (en) * 1977-02-02 1980-03-04 Hitachi, Ltd. Turbine rotor construction
DE69704001D1 (de) 1996-05-09 2001-03-08 Rolls Royce Plc Dämpfungsstifte für Deckbänder von Turbomaschinen
DE10256778A1 (de) 2001-12-11 2004-01-08 Alstom (Switzerland) Ltd. Schwingungsdämpfer
JP2008045419A (ja) * 2006-08-11 2008-02-28 Mitsubishi Heavy Ind Ltd インテグラルシュラウド翼のせん断応力低減構造
EP2019188A1 (fr) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Etage de rotor comprenant un dispositif d'amortissement

Also Published As

Publication number Publication date
US20110299989A1 (en) 2011-12-08
CN102317578A (zh) 2012-01-11
WO2010094540A1 (fr) 2010-08-26
EP2399005B1 (fr) 2012-11-21
EP2399005A1 (fr) 2011-12-28

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