WO2010094540A1 - Groupe d'aubes d'une turbomachine - Google Patents

Groupe d'aubes d'une turbomachine Download PDF

Info

Publication number
WO2010094540A1
WO2010094540A1 PCT/EP2010/050936 EP2010050936W WO2010094540A1 WO 2010094540 A1 WO2010094540 A1 WO 2010094540A1 EP 2010050936 W EP2010050936 W EP 2010050936W WO 2010094540 A1 WO2010094540 A1 WO 2010094540A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
coupling element
shroud
vibrations
tip
Prior art date
Application number
PCT/EP2010/050936
Other languages
German (de)
English (en)
Inventor
Christoph Hermann Richter
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US13/201,893 priority Critical patent/US20110299989A1/en
Priority to EP10702854A priority patent/EP2399005B1/fr
Priority to CN2010800081780A priority patent/CN102317578A/zh
Publication of WO2010094540A1 publication Critical patent/WO2010094540A1/fr

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
    • F01D5/12—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
  • the flow medium is steam in steam turbines.
  • the flow medium is steam in steam turbines.
  • the flow over the streamlined blades causes vibration of the blades, which leads to disturbing effects.
  • a blade could be damaged in the form of a crack. Therefore, efforts are being made to modify the blades so that vibrations are avoided or damped so that no damage to the blades occur.
  • Vibrations in the area filled with granules lead to movements of the granules. Since this movement is accompanied by internal friction, it is also associated with a damping.
  • nodal diameter vibrations form. These node diameter vibrations are characterized in that over the circumference of the blades, the amplitudes of the vibrations have a sinusoidal shape.
  • adjacent blades there will be a relative rotation with respect to the immediate or distant neighboring blades.
  • An advantage of the invention is that such relative rotations the immediate or distant neighboring blades are damped according to the invention.
  • 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 in the
  • Blade tip is arranged.
  • 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 has 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.
  • Shrouds are disposed on the blade tips and have a construction that is comparatively large to the overall bucket.
  • this shroud is the coupling element firmly arranged. This can be done for example by a soldering, a screw or riveting.
  • the second blade tip which belongs to the adjacent blade, has 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, the greater the vibration amplitudes at the tip.
  • the material should be chosen such that it can be connected as rigidly and firmly as possible with the blade, wherein the strength values of the coupling element should be such that the coupling element itself can hardly perform its 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.
  • Bucket on which the coupling element is fixed, entrains well enough. Effective damping is possible.
  • Figure 1 shows a detail of an arrangement seen in the radial direction, with a view of the shrouds.
  • Fig. 3 is a perspective view of a shroud.
  • FIG. 1 shows a detail of an arrangement in the radial direction. D. h., The radial direction is perpendicular to the 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 formed in the radial direction elongated and are flowed during operation via a flow medium not shown in detail, wherein the first blade 1 and the second blade 2, a rotation in a direction of rotation 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 for example be firmly connected 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 to be minimized, which takes place in that the coupling element 5 on the second blade 2 is present.
  • 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 is not shown in detail in FIG.
  • 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.
  • 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 such 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)

Abstract

L'invention concerne un système d'amortissement destiné à amortir les oscillations d'un groupe d'aubes, dans lequel des aubes adjacentes sont accouplées l'une à l'autre par l'intermédiaire d'un élément d'accouplement (5). L'élément d'accouplement (5) est agencé fixement dans une première aube (1) et fait saillie dans la seconde aube (2). L'élément d'accouplement n'est pas agencé dans la seconde aube, mais repose simplement sur cette dernière de sorte que, en raison de forces centrifuges, une extrémité libre (9) de l'élément d'accouplement (5) soit pressée contre la seconde aube (2), générant une force de friction qui conduit à une dissipation d'énergie, ce qui amortit les oscillations.
PCT/EP2010/050936 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine WO2010094540A1 (fr)

Priority Applications (3)

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

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP09002224A EP2218875A1 (fr) 2009-02-17 2009-02-17 Bandage d'aube dans une turbomachine
EP09002224.5 2009-02-17

Publications (1)

Publication Number Publication Date
WO2010094540A1 true WO2010094540A1 (fr) 2010-08-26

Family

ID=40874982

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/050936 WO2010094540A1 (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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2586980A3 (fr) * 2011-10-24 2018-01-24 United Technologies Corporation Amortisseur de rail de pale de turbine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4784571A (en) * 1987-02-09 1988-11-15 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
JPH08303205A (ja) * 1995-05-11 1996-11-19 Hitachi Ltd タービン動翼
DE69704001T2 (de) 1996-05-09 2001-05-23 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

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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.
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-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.
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
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
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
JPS5395406A (en) * 1977-02-02 1978-08-21 Hitachi Ltd Connection structure for vane
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
FR2612249B1 (fr) * 1987-03-12 1992-02-07 Alsthom Aubage mobile pour turbines a vapeur
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
EP2019188A1 (fr) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Etage de rotor comprenant un dispositif d'amortissement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4784571A (en) * 1987-02-09 1988-11-15 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
JPH08303205A (ja) * 1995-05-11 1996-11-19 Hitachi Ltd タービン動翼
DE69704001T2 (de) 1996-05-09 2001-05-23 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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2586980A3 (fr) * 2011-10-24 2018-01-24 United Technologies Corporation Amortisseur de rail de pale de turbine

Also Published As

Publication number Publication date
CN102317578A (zh) 2012-01-11
US20110299989A1 (en) 2011-12-08
EP2399005B1 (fr) 2012-11-21
EP2218875A1 (fr) 2010-08-18
EP2399005A1 (fr) 2011-12-28

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