EP2399005B1 - Groupe d'aubes d'une turbomachine - Google Patents

Groupe d'aubes d'une turbomachine Download PDF

Info

Publication number
EP2399005B1
EP2399005B1 EP10702854A EP10702854A EP2399005B1 EP 2399005 B1 EP2399005 B1 EP 2399005B1 EP 10702854 A EP10702854 A EP 10702854A EP 10702854 A EP10702854 A EP 10702854A EP 2399005 B1 EP2399005 B1 EP 2399005B1
Authority
EP
European Patent Office
Prior art keywords
blade
coupling element
shroud
tip
blades
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.)
Not-in-force
Application number
EP10702854A
Other languages
German (de)
English (en)
Other versions
EP2399005A1 (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 EP10702854A priority Critical patent/EP2399005B1/fr
Publication of EP2399005A1 publication Critical patent/EP2399005A1/fr
Application granted granted Critical
Publication of EP2399005B1 publication Critical patent/EP2399005B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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.
  • 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.
  • 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 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 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.
  • the shrouds are arranged on the blade tips and have a construction which is comparatively large to the overall blade. In 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, 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 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 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.
  • 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.

Claims (4)

  1. Dispositif
    comprenant une première aube (1) et une deuxième aube (2) disposée au voisinage de la première aube (1),
    dans lequel un élément (5) d'accouplement est monté fixe dans la première aube (1) et une partie de l'élément (9) d'accouplement s'applique à la deuxième aube (2),
    dans lequel la première aube (1) a une première pointe d'aube,
    dans laquelle la deuxième aube (2) a une deuxième pointe d' aube,
    dans lequel l'élément (5) d'accouplement est disposé dans la zone des première et deuxième pointes d'aube,
    dans lequel la première pointe d'aube a un premier anneau (13) de renforcement et l'élément (5) d'accouplement est monté dans le premier anneau (13) de renforcement,
    dans lequel la deuxième pointe d'aube a un deuxième anneau (14) de renforcement,
    dans lequel le premier anneau (13) de renforcement et le deuxième anneau (14) de renforcement ont respectivement une fente (11) dans laquelle est monté l'élément (5) d'accouplement et la fente (11) est disposée latéralement dans le premier anneau (13) de renforcement et dans le deuxième anneau (14) de renforcement,
    caractérisé en ce que l'élément (5) d'accouplement est monté d'une manière lâche dans le deuxième anneau (14) de renforcement.
  2. Dispositif suivant la revendication 1,
    dans lequel l'élément (5) d'accouplement est oblong et étroit.
  3. Dispositif suivant la revendication 1 ou 2,
    dans lequel l'élément (5) d'accouplement est une tôle.
  4. Dispositif suivant l'une des revendications 1, 2 ou 3, dans lequel l'élément (5) d'accouplement a, considéré en section transversale, une forme rectangulaire ayant une largeur L et une hauteur H,
    dans laquelle L est plus grand que H et l'élément (5) d'accouplement est disposé dans l'anneau (10, 13, 14) de renforcement de manière à ce que la surface s'applique par la largeur L en fonctionnement à l'anneau (14) de renforcement.
EP10702854A 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine Not-in-force EP2399005B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10702854A EP2399005B1 (fr) 2009-02-17 2010-01-27 Groupe d'aubes d'une turbomachine

Applications Claiming Priority (3)

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

Publications (2)

Publication Number Publication Date
EP2399005A1 EP2399005A1 (fr) 2011-12-28
EP2399005B1 true EP2399005B1 (fr) 2012-11-21

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 Before (1)

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

Family Cites Families (20)

* 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.
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
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
GB9609721D0 (en) 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper
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
CN102317578A (zh) 2012-01-11
WO2010094540A1 (fr) 2010-08-26
EP2399005A1 (fr) 2011-12-28
US20110299989A1 (en) 2011-12-08
EP2218875A1 (fr) 2010-08-18

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